CN87104303A

CN87104303A - Advanced instrument landing system (ILS)

Info

Publication number: CN87104303A
Application number: CN87104303.3A
Authority: CN
Inventors: 约翰·P·奇泽姆
Original assignee: Sundstrand Data Control Inc
Current assignee: Sundstrand Data Control Inc
Priority date: 1986-05-15
Filing date: 1987-05-15
Publication date: 1988-03-02
Also published as: AU600740B2; ZA873358B; CA1296794C; AU7694387A; IL82496A0; WO1987007030A1; CN1009964B

Abstract

A kind of system that is used for aircraft landing, it has utilized by an earth station and a machine of gps system time synchronized and has appeared on the stage.Earth station comprises the transmitter of a radiation signal sequence, this burst provides accurate pilot signal to aircraft, machine is appeared on the stage and is comprised a radio receiver and a processor, be used to receive and handle the pilot signal that is sent out, in order to provide indication to help aircraft landing to the driver when the aircraft landing, also comprise on the machine GPS receiver and ground GPS receiver to produce the signal of represent the gps system time, comprise that a channel to channel adapter on the machine makes itself and earth station transmitter synchronous in order to the startup processor.

Description

The present invention relates to a kind of advanced person's instrument landing system (ILS), more particularly, be about the improvement of the landing system of radiation same frequency pilot pulse in certain sequence of all earth stations of a class, this improvement makes a kind of like this earth station of same frequency landing system engrave radiation when the appointment in the definite clock system, and make this earth station can by one not only known so specific appointment constantly, but also can obtain to utilize this aircraft when participating in the cintest of determining the clock system time to discern uniquely.This improvement has also provided a Precise Distance to land station to aircraft.

Be positioned at away from other at an earth station of single-frequency landing system under similar the situation, this earth station need not in the radiation of the moment of an appointment, and aircraft also is not difficult to discern this earth station when participating in the cintest.Yet,, must provide and discern at least one such same frequency platform uniquely to get rid of the means of contiguous other if there have a plurality of similar Landing stages to be compared to each other on the geographic position of a compactness to be approaching.

In common landing system, for example as in common instrument landing system (ILS) and FAA microwave landing system (MLS), by frequency assignation different in the wave band is given each different platform and with airborne equipment be tuned to realize unique identification and the signal exchange between the aircraft and a specific earth station when participating in the cintest on the frequency of selected platform.EAA MLS system has 200 individual channels for its use on the frequency range of 5000 to 5250 megahertzes, the ILS system has about 40 passages in the paired channel for its use in 100 to 300 megahertz range.Therefore, the proper number of the channel that can discern respectively of unifrequency landing system is shown it is between 40 to 200 passages.The patent No. at me is 4429312, is entitled as in the United States Patent (USP) of " monitoring system of independently landing ", discussed a kind of different types to one with the identification of Landing stage frequently, therein,, be transmitted into some signals on the aircraft by pulse code in order to discern this.When aircraft be in the isolated remote districts of other land station and when aircraft have weather radar in order to inquiry land station, with radar add together a decoding scheme and in aircraft cockpit one be used for that land station selects suitable password selection converter the time, this system generally is gratifying.

Yet not all aircraft all has the weather radar that is used to inquire earth station.In addition, if when on approaching geographic position, having several airports or same airport to have several such Landing stages, these same frequency signals from all such landing systems can arrive aircraft simultaneously, therefore, for the single distance tracking identification and the purpose of channeling conduct, these signals can not suitably separatedly come.This is to be air traffic control basically, and by the same problem that the employed common air traffic radar beacon system of FAA (ATCRBS) is run into, it is called as " obscuring ".Thereby the described weather radar technology that has corresponding recognition code of my U.S.4429312 patent is the remote place that is suitable for very much such as the such isolation of offshore oil drilling cramp, do not have a plurality of closely places of adjacent same frequency landing system but be suitable for.The appearance of this problem mainly is owing to radar on these systems and the machine all uses a such factor of common frequency.Therefore, have no idea to remove to trigger uniquely a specific platform for clear and definite identifying purpose.Therefore, always exist the risk that is not the contiguous platform of the triggering making us wishing, the result is that this aircraft can be received simultaneously and causes the response of obscuring to aircraft from two positions.

Except the method for the earth station that can discern a specific same frequency uniquely, concerning a landing system, very the characteristic of Xi Wanging is to have the ability that range information is provided.Range data has the main application of three aspects at least:

1. be used to warn a kind of means of pilot near the touchdown point degree;

When aircraft when the distance of touchdown point diminishes, in order to keep closed loop stability, range data can be used for reducing automatically the means (usually being called as " process is softening ") of Landing stage gain; And

3. as utilizing the elevation data that provides by landing system to determine that aircraft is in a kind of means of runway height in the landing mission.

In common ILS system, generally some definite distance De Biao Chi beacon stations provide by being separated by with the point that lands on the ground to the distance of the point that lands.The vertical fan-shaped beam that these beacon station radiation landing aircrafts will pass, the range information that obtains like this on the machine are used for warning the pilot and are used for " process is softening ".

In the practical application of FAA MLS and common ILS, another kind of more accurate distance measure is common TACAN/DME(Tacan/stadimeter of all being furnished with by nearly all aircraft) interrogator provides.One of TACAN/DME device inquiry and MLS or ILS earth station are put DME beacon station together on the machine, and utilize common DME technology from direct distance measure of this beacon station reception.

Under some lands application, need a very accurate distance measure, for this purpose, adopted an accurate DME(to be commonly referred to PDME).PDME is similar to common DME, adopts the pulse of faster rising edge to obtain higher precision.This PDME system has increased the burden that corresponding PDME airborne equipment is installed for the aircraft that must make it for the very accurate range observation that obtains needs on machine.Another technology that is used for obtaining Precise Distance in landing system is the technology instruction that is provided by my U.S.4429312 patent.In the disclosure content, range observation is to be obtained by the earth station of weather radar inquiry landing system and the transmission of trigger pulse angle pilot signal.These pulse reply signals be with the inquiry of weather radar synchronous and with common mode to its distance tracking with provide aboard the precision distance.Pulse with the fast rise edge can obtain the more range observation of high precision.

The method of aforesaid two kinds of identification earth stations (be frequency select or pulse code) all need optional equipment and or be used for be tuned to the frequency or be used to of earth station select from adjustable driving cabin control of the decoding method of the signal of that land station's radiation.In addition, Cai Yong Biao Chi beacon station or DME platform carry out range observation, and suitable De Biao Chi beacon station or DME beacon station need be arranged at landing system earth station place.Very Jing Mi range observation need increase the PDME equipment on special aerial and ground, weather radar all is equipped with need additional PDME equipment and utilize weather radar to provide Precise Distance (as instructing in my the U.S.4429312 patent) to eliminate, but not all aircraft.Therefore, all common landing systems have all trended towards need increasing the control device of airborne equipment or driving cabin or increasing the two simultaneously, so as to obtain with selected earth station unique get in touch and from its distance.

Except the technology of two kinds of acquisition distances discussed above (be the aircraft inquiry emission of passing mark Chi beacon station and survey aircraft with aircraft from the past time of replying between the reception that the impulse repeater at landing system obtains), timing station technology in addition.This technology can utilize high precision and low precision clock to realize.For example, an equipment that participates in the unit on land station of picture or the machine in the station, signal of the known moment emission of in a definite very Precise time system one is at second unit, measure this time of reception that transmits such as the equipment on the aircraft in same definite clock system; Owing to know the time that transmits, thus the travel-time of signal between two stations thus just the distance between two stations just can calculate.A known application of this timing distance-finding method is USAF AN/APN-169, the maintenance equipment (SKE) of standing (Station Keeping Equipment).

Another method of setting up a common clock time is to participate in the unit to each to load onto the low clock with nominal degree of stability of price, also make these Zhong Yuyi common time references synchronous termly.Some low price clocks can be realized by an initial general two-way ranging process synchronously like this, this two-way ranging process has been determined the distance between the participation unit, utilizes measured range data by the exchange that participates between the unit at related clock time then.Like this, each low price clock that participates in the unit is synchronous to the clock adjustment on the selected aircraft in all participation aircrafts.This synchronizing process repeats with the periodic time interval then, and this time interval should frequently occur so that this common time reference keeps enough precision.All clocks are that the mean value of all clock times is synchronous when all clocks are begun synchronizing process to a distortion of the method for the clock synchronization of a selected unit.

Therefore, this " on the spot " synchronizing process needs accurate range finding and exchanges data or communication system, comprises that each participates in the transmitter and receiver in the unit.Needing clock synchronization device on all aircrafts is not (being expense, weight and complicacy) of making us wishing in many application.

One of advantage of utilizing common clock system is to realize identification by utilizing " time gap ".In the design in this ETAD expected time of arrival and departure slit, each participates in the designated specific radiation clock time in unit, and this clock time repeats with particular time interval.For example, a specific participation unit, as No. 3, can radiation when the 3rd second of per minute.With this radiation on a special time combined be that subsequently other participates in the time interval or the time gap that unit must not radiation, thisly just allow other to participate in unit to receive its emission, identification (must be to come to specify in the participation unit of launching in this time interval promptly) in any emission of receiving in this time interval in order to realize this emission transmitter by participating in definite clock time of unit by using and corresponding time gap to its regulation.Utilize the time gap of an appointment or time period to provide a shielded recognition methods to regard as and be similar to the different frequency of utilizing an identification usefulness, use at other station that this frequency can not be in the specific geographic location area.

Though it is that use to determine and have precision and both can provide precise distance measurement for precision interval clock time of part microsecond order of magnitude, can provide unique identification again, but such one of current use is subjected to highly stable clock jointly with clock time precision, as atomic clock, the expense of bringing and the restriction of complicacy perhaps are subjected to the expense of the required synchronizer of lower price clock (being communication system etc.) and the restriction of complicacy.

Think widely, because the work at place, all locations normally carries out on an independent frequency, so landing system does not originally need to use a plurality of frequencies.Single-frequency work is an advantage, because if actual talk down system can be operated on the same frequency different sites, the complicacy of airborne equipment and price just may greatly be simplified so.For example, receiver can be the device of a fixed frequency on the machine.

Therefore, should be realized that, be installed in an IFR(instrument flight control when only using) during airborne equipment on the aircraft, in the landing system of a fixed frequency, just needing one not only can provide the station to select but also can provide the landing system of ranging data.And a such system should be simple and low price.Except the aircraft of minimum, on all aircraft all reality increased " nautical star " (NAVSTAR) or " global location " (Global Positioning System) (GPS) under the situation of guider, also wish very much to find the method for utilizing GPS, provide channelizing (i.e. identification) and range data for the landing system of single-frequency.This point is because the so intrinsic low price of some fixed frequency landing systems and can find in more place all over the world and become actual especially.Therefore just there is the instrument guidance system that needs an advanced person.

According to one embodiment of the invention, provided a landing system, it comprises that each earth station and machine that is equipped with the GPS receiver appears on the stage, this receiver produces a trigger pip of representing the gps system time, the earth station of a Radiation Emission burst, this sequence comprises the accurate guidance information that helps aircraft landing, and the machine with receiver and processor is appeared on the stage, this processor is used for these accurate pilot signals of conversion, the indication that provides vector aircraft to land to the aviator.More particularly, the trigger pip of being come by the GPS receiver on the earth station is further processed, and provides one second trigger pip or pumping signal on a special time to a specific earth station appointment.As response to this pumping signal, this earth station radiation aircraft pilot signal.In airborne, be further processed with the trigger pip that the GPS receiver obtains by machine, on a specific time, (promptly be equivalent to select a hope to accept the specific land station of landing guidance there and select a time interval or time gap from it, at this moment can be in the interbody spacer from selecteed like this land station received signal effectively) this processor of excitation is provided, make its produce the signal of landing guidance information.The technology of this use gps clock time is because this clock time need not increase expense to the GPS receiver and just can obtain, so this technology provides reliable identification to the land station of the low price unifrequency landing system that is selected.

In a specific embodiment of the present invention, comprised a range finding reference signal from the burst of earth station radiation, these range finding reference signals and the pilot pulse that is associated are that the gps clock time-triggered signal that is produced on the aircraft is repeated synchronously when being received on machine.So the time that the range finding reference signal is received aboard can measure with common synchronic distance tracking circuit, so can accurately calculate the distance between aircraft and the earth station.Therefore, the gps clock time provides the Precise Distance data of a selected low price unifrequency land station.

Along with the appearance of GPS, accurate synchronized machine will become very usual with clock in aviation aircraft.Can obtain such generalized time and make that it is very suitable considering to use such clock technology with more wide scale.Some other advantage of the present invention and feature will be found out from detailed description of the present invention, the embodiment that exemplifies, accompanying drawing and claim significantly.

Fig. 1 is the calcspar as the advanced person's of theme of the present invention landing system.

Although the present invention can have many multi-form embodiments, in the accompanying drawings with following, only describe in detail and illustrate a specific embodiment, but, should be appreciated that present disclosure should be considered to explain an illustration of the principle of the invention, rather than plan Limit the invention on the specific embodiments of this usefulness figure explanation.

The embodiment of this recommendation of advanced landing system is explained with reference to the landing system of my U.S.4429312 United States Patent (USP) and is described. , should be appreciated that, the invention provides the technology that can be applied in the many different landings system, therefore, it is not limited to the improvement to diagram in that patent and the accurate landing of that class system described.

As that patent illustrated and in wherein the 8th and the 9th row described, the system of this granted patent provides an accurate landing guidance platform based on ground, this is from separate antennas radiation landing directional beacon and glide slope lead beam, these antenna directly points to the landing aircraft along the land route, this landing directional beacon and lead beam are received on machine and handle to obtain to provide to the pilot signal of the indication of landing.In the illustrated system of that patent, should be based on the system on ground or can be triggered generation and synchronous the replying of certain reference signal, the signal Synchronization that receives with weather radar for example, perhaps this system also can free-running operation, and only received and utilize by a landing aircraft.Before this a kind of system of pattern be present improvement at system, therefore, the free running mode of landing system works will thoroughly not discussed.

Get back on Fig. 1, the landing system that drawn of there comprises that an earth station and a machine appear on the stage, earth station comprises two directional antennas 21 and 22 with accurate guiding positioning antenna wave beam Figure 23 and 24 that are used for the guiding of horizontal direction aircraft, and its xsect indicates with B and C.This earth station also comprises an omnidirectional antenna 5 that produces omnirange Figure 25.These

antenna

5,21 and 22 is connected on the radar transmitter 32 by a switch 26 and cable 27.Regularly and on-off circuit 29 gauge tap 26 and start the output of transmitter 32.

Two paired

glide slope antennas

33 and 34 directional antenna directional pattern be aligned and overlap respectively in the above and below of a predetermined glide slope (normally 3 degree), make when aircraft exactly when glide slope lands, the signal that receives from these

twin aerials

33 and 34 on the machine will equate.

In vertical direction glide slope guiding, this earth station comprises that also two are used for paired accurate glide slope lead beam 33a of radiation and the

directional antenna

33 and 34 of 34a, and its xsect indicates with D and E.These two

antennas

33 and 34 are linked on the transmitter 32 by duplexer 26 equally.The

antenna

23 and 24 the paired beam pattern that are used for horizontal direction guiding are overlapping, thereby make the centre line C L of extending along runway provide the signal of equal intensities.Therefore, if the signal intensity of two antennas that receive on machine equates that then aircraft necessarily is positioned at the top of runway centerline in the horizontal direction.

For a landing on the landing route, four pilot signals of all that receive on the aircraft will equate.; these paired signal imbalances that desirable landing route upper and lower or left and right departing from will causing receiver place is received; indicate the direction that aircraft has departed from projected route to the driver, this course of work has been carried out thorough description in my U.S.4429312 patent.

According to that patent, the machine of this system is appeared on the stage and is drawn in the right of Fig. 1, has comprised a radar receiver 8 and antenna 3.This radar receiver 8 is connected on a range gate and the navigating processor 15, and this processor 15 provides range data to a range reading display 18 and a route deviation indicator that is attached thereto.

By sending a trigger pip T2 to trigger the once emission of earth station to timing and on-off circuit 29.Current emission contains a plurality of bursts that transmitted successively.At first, timing and on-off circuit 29 send a coded pulse group reference signal A by omnidirectional antenna 5 by transmitter 32.The intensity of this reference signal is used for the gain of receiver 8 on the setting machine, thereby operation of receiver is at the linear segment of its resonse characteristic on the maintenance machine.After a fixed delay that is determined by timing and on-off circuit 29, switch 26 stepping is in order connected four directional antennas 21 successively with

transmitter

32,22,33 and 34 produce emission, comprise left and right paired directional beacon pulse and upper and lower paired glide slope pulse.These pulses once produce one, and suitable delay is arranged between the pulse.As explaining in my the U.S.4429312 patent, adjustable attenuator 44 plays the balanced antenna excitation, makes that these pilot signals all have equal amplitude when aircraft accurately is on the landing route.The sequence of these four pilot signals is to pre-determine with changeless, thereby makes aircraft discern these signals by their order in this sequence.

By these accurate lead beam B among Fig. 1, C, the pulse of D and E emission adds the reference signal group A from omnidirectional antenna, is sent to processor 15 on the machine for the aircraft antenna reception and by receiver 8.Processor 15 is programmed to utilize reference signal A to determine distance, and it is presented on the range reading display 18, and utilize accurate approaching signal B, C, D and E produce the output signal of expression aircraft with respect to the position of the landing route of hope, and it is delivered on the off-course deviation indicator 20.

Use description to discern uniquely the equipment of the earth station among Fig. 1 now.The earth station of Fig. 1 is equipped with 60, one gps antennas that link to each other with receiver 62 of a GPS receiver/computing machine and a time gap selector switch 64.GPS receiver/computing machine 60 utilizes GPS or NAVSTAR(nautical star) satellite system 66 provides accurate geographic position.Earth station only needs to join a receiver that is suitable for providing the output signal T1 that represents the gps system time fully.Utilize such receiver becoming more and more common." Aviation week in version on November 4th, 1985; Space Technology " the 58th page on be entitled as in " global location as Civil Navigation Aids System ", the equipment that is suitable for has been provided popular description.Time gap selector switch 64 utilizes the output signal T1 of gps system time to form a trigger pip T2 who is used for timing and switchgear 29.Each earth station all has the unique time gap or the passage of an appointment, thus the emission energy that makes it from around or make a distinction near the emission of land station.The time break joint selector switch 64 sending this signal T2 on the time for a specific gps clock discerning land station's specific land station regulation uniquely to this.The number of times that must produce trigger pip T2 p.s. depends on aircraft in order to have the speed of enough required pilot signals of guiding closed loop stability, and nominal value is p.s. 20 times.Timing and on-off circuit 29 place switch 26 on the tram, and time-delay is provided, and the omnidirectional coding reference signal A of stimulated emission machine 32 transmissions, then send two and form right phasing signal B, C and D, E.

Facility on the present let us machine, as the situation of earth station, aircraft only need be equipped with a GPS receiver/computing machine that the output signal T1 that represents the gps system time simply can be provided.This receiver 68 also is furnished with a suitable antenna 70, and the output of receiver is connected on the time gap selector switch 72.In order to receive the earth station of a selection, golden hour slit selector switch 72 can be transferred on the passage that any one driver wishes, this earth station is with reference to the accompanying drawings corresponding to the passage of the earth station among Fig. 1.In case time gap selector switch 64 is transferred to this relevant land station, the synchronous pilot signal of returning from earth station by aircraft antenna 3 and aircraft receiver 8 is owing to adopt the disposal route of time gap gate to become separable, and, just become and to have discerned to the return signal of aircraft as relevant land station owing to be different from from other surface facility of near zone synchronous landing guidance signal with the same frequency of same frequency emission.

The time that enters duty is known because the transmitter 32 of selected earth station is triggered, and because receiving the used time of this synchronized transmissions signal aboard can be measured, range gate and navigating processor 15 can easily calculate the distance between aircraft and the earth station, and this distance may be displayed on the digital indicator 18 of aircraft cockpit.If GPS receiver/computing machine of installing aboard is " computing machine completely " (a full computer), so just can obtain the output signal PA of a representative aircraft with respect to the earth surface geographic position.Because relevant earth station fixes on the ground, thus can utilize the position PG of this earth station and the position signalling PA of aircraft together, with the direct reading 18 that obtains distance between an aircraft and this earth station '.This reading can be used for by measuring intersection benchmark or the check transmit and receive the reading 18 that the time between the signal obtains aboard.Therefore it also can be used as the intersection benchmark or the check of instrument with elevation information in order to determine the position of glide slope.In addition, it can be used for the height indicator of cross-check aircraft with glide slope information.

The accuracy of timekeeping of gps clock time-triggered signal T1 is the restriction that is subjected to the circular error probability (CEP) of GPS.Common P sign indicating number and the expection of the circular error probability (CEP) of C/A sign indicating number are 10 to 50 meters.The CEP precision of differential P sign indicating number and differential C/A is 2 to 6 meters in typical case.Because the CEP(circular error probability of the GPS that causes by the propagation delay of ground and the place's the unknown of aircraft platform), thereby that is the system clock error of GPS, should be identical, suppose and use similar GPS facility, so by measuring gps clock that gps clock time that pilot signal is launched from ground and this signal be received difference or the interval (being the timing distance measure) and the distance that obtains can make these unknown errors offset between the time aloft.Therefore, timing distance measure precision should be consistent with the positional precision of differential GPS (promptly than common good).In other words, though we only use a common GPS receiver just to obtain surprising result, promptly utilize gps time to come the channelizing result to obtain being tending towards the measured value to the some distance of landing of differential GPS measured value.

The professional in present technique field can understand, fabulous range measurement accuracy is crucial to landinging control, particularly important particularly those that carry out center line guiding with a surface beacon platform that departs from out for hope are used, this is particularly useful in Military Application.The center line guiding can obtain by the signal of service range display 18 and route deviation indicator 20.

Can come uniquely and the number of the land station of identification effectively by the time gap technology of using gps clock time and associated, can determine by considering following factors:

(1) two land stations that do not have transmitted in the enough approaching each other time, make signal from a land station can arrive on the airplane and be can be detected, thereby might produce the landing guidance signal of a falseness in to the time gap of another land station's appointment.For fear of this thing happens, must determine at first that an aircraft can be effectively from the aircraft of land station's detection signal and the distance between this land station.Suppose that this distance is 80 miles, so general in such field, just can not there be two at the speed of the radio frequency propagation of multiply by every mile 6 microsecond than 80 miles that point out or about 500 microseconds transmit steering signal in the more approaching time.If do not take these preventive measure, signal from two land stations can reach same airplane during processor is triggered the time gap G2 that produces the landing guidance signal so, therefore not to cause to obscure, provide the vectoring information of vector aircraft exactly towards wrong land station.

(2) another factor of this respect is that each land station preferably should launch 20 pilot pulses p.s. to keep the stability of guiding closed loop.So this means that each land station must during this period, not have other land station's emission by distributing to its 20 * 500 microsecond or 10000 microseconds p.s. in 80 mile range of pointing out.Typical hereto example case, this 10,000 microsecond or 0.01 second total time interval must be by distributing to each land station each second.This shows can only settle 100 unique discernible land stations in 80 miles scope.Therefore, as practical application, notice that 100 single groups discerning launch time at least can be used for being identified in any one in the earth station of 100 same frequencys in the 80 mile radius scopes singlely.This number is enough had a surplus, because as previously mentioned, only there are 40 channels that are used for discerning uniquely in common ILS system.

At last, processor 15 can be equipped with a narrow range gate and follow the tracks of the omnirange signal A of earth station and paired signal B and C on the machine, and D and E.Use the route deviation indication display 20 of vision, phasing signal is treated to provide accurate guiding to the driver.But, occasionally, may fall among the range gate from other same frequency signal of the chosen Landing stage in this scope or other Landing stage (for example homogenous frequency signal that is produced by my the described system of U.S.4429312 patent).Because these homogenous frequency signals occur comparatively speaking occasionally, and be nonsynchronous for gps time, so, if with its with from the desirable signal phase average of selected earth station, its influence will be small.All be stored in the memory of computing machine by the signal that drops in the range gate that all are received, and purpose in order to guide, only utilize those interior storage signals of regulation boundary of the arithmetic average value that drops on all signals, just this small influence further can be reduced to minimum.This is called as " disordered point " montage (" Wild-Point editing ").

The embodiment of also describing illustrated in the present invention is not limited to is because can make many variations in the scope of following claim.For example, the technology of my U.S.4429312 patent can be used simultaneously with the technology described in the present patent application.Thisly use useful especially when carrying out the transition to GPS (earth station can be launched) simultaneously on a clock basis and as to the inquiry of weather radar or the response of self-operating.Therefore, should be realized that, about here as an example the particular device of explanation do not prepare as any restriction or be inferred to be restriction.Certainly, plan to go topped all such improvement that drop in the claim scope with appended claim.

Claims

1, a kind of aircraft that makes includes along a system of being landed by the best landing guidance route of predetermined glide slope and center line regulation:

(a) one or more earth stations, each includes a transmitter, receive a trigger pip and work, be used for that this transmits and comprises accurate pilot signal by the directional guide aerial radiation that points to along guiding route to sequence that transmits of aircraft radiation;

(b) machine is appeared on the stage, and comprises receiving said radio device that transmits and processor device, in response to a pumping signal, said the transmitting of processing, so that be provided for the guiding indication that vector aircraft lands;

(c) at the appear on the stage GPS receiver at place of each ground and machine, be used to produce the gps signal of representing the gps system time;

(d) at the synchronous device at each earth station place, work, be used to produce the trigger pip of a said transmitter of excitation in response to said gps signal; And

(e) synchronous device of appearing on the stage and locating at each machine is worked in response to said gps signal, is used to produce the trigger pip of a said processor device of excitation,

Thus, received for gps time synchronous transmit also synchronous to the work of said processor device.

2, the system as claimed in claim 1, wherein said earth station synchronous device comprises the time gap selecting arrangement, be used to time of selecting said transmitter pumping signal to be produced, play the gps system time, this launches each earth station base on the time of appointment.

3, system as claimed in claim 2, the wherein said machine synchronous device of appearing on the stage comprises the time gap selecting arrangement, be used to select the time interval of gps system time, in the time interval of this selection, said processor device is driven handles the said sequence that transmits.

4, system as claimed in claim 3, the wherein said time interval is with the said beginning that transmits of land station's radiation of a selection, and

The wherein said time interval continues a sufficiently long time span, is enough to guarantee to receive transmitting by the said selected land station in the predetermined work scope.

5, system as claimed in claim 4, wherein the fixed time of said land station is by being that adjustable said time gap selector installation is determined for transmitting of other earth station, make radiation for said selected land station, be enough to get rid of from transmitting of other land station at one and disturb on the time span of the suitable processing that transmits from selected land station, do not allow other land station's radiation.

6, the system as claimed in claim 1 wherein is radiated the sequence that transmits on the aircraft by a land station and comprises that is received a reference signal of launching after the said excitation trigger pip by earth station; And

Processor device comprises according to the gps system time that receives and the time interval between the said reference signal and determines the device of aircraft to said earth station distance on the wherein said machine.

7, system as claimed in claim 3, processor device comprises the range gate tracking means on the wherein said machine, this device is in response to said time gap selecting arrangement, and arrive time of aircraft in response to said reference signal and said accurate pilot signal, if in order to repel by said radio device receive drop on times selected at interval in and can produce the signal of irrelevant guiding indication to its processing.

8, system as claimed in claim 6, wherein each earth station comprises the antenna of an isotropic directivity, and said reference signal is by the omnidirectional antenna radiation of said earth station by it.

9, system as claimed in claim 6, wherein said reference signal by each earth station radiation is encoded, and is used to discern each earth station.

10, the system as claimed in claim 1, wherein said guiding antenna at each earth station place comprises that a plurality of paired arrangements and radiation are the directed radiation device of paired lead beam to guiding route, said directed radiation device comprises overlapping paired directional beacom radiation appliance, this device points to the relative both sides of center line on the surface level, the glide slope radiation appliance that also comprises overlapping pairing, this device points to the above and below of said predetermined glide slope; And

Wherein each earth station comprises signal timing and switchgear, utilizes said transmitter pumping signal, different radiation appliances is coupled on the transmitter, by each directional beacom and each pilot signal wave beam in succession of glide slope radiation appliance radiation.

11, system as claimed in claim 10, wherein each machine is appeared on the stage and is comprised and be used to refer to the device indicating that aircraft departs from the landing route, and

Wherein said processor device

(a) in response to the said pilot signal that receives by said radio device, and in response to the time location in each burst;

(b), and compare the right intensity of these signals with received pilot signal wave beam pairing;

(c) said device indicating is produced and transmits the output signal that is used to indicate to said landing guidance route deviation.

12, the system as claimed in claim 1, the GPS receiver during wherein said machine is appeared on the stage comprise the device that is used for determining said aircraft geographic position, thus, under the situation of knowing the earth station geographic position, can determine the distance between this aircraft and the earth station.

13, the system as claimed in claim 1, the GPS receiver that wherein said machine is appeared on the stage comprises:

In response to receiving mistiming between the said accurate pilot signal on the generation of said trigger pip and the said aircraft, being used for determining the device of the distance of said aircraft to an earth station.

14, the system as claimed in claim 1, wherein the said GPS receiver in said earth station is positioned at a known position and comprises:

(a) in response to the received signal that comes from a constellation of satellite, be used for determining the device of said earth station position;

(b) be used for measuring the device of difference between said known location and the said definite position; And

(c) be used to store and characterize the device of the correction signal of said position difference to the emission of appearing on the stage of said machine.