CN1160210A - Apparatus for detecting that flying object has passed monitoring space - Google Patents
Apparatus for detecting that flying object has passed monitoring space Download PDFInfo
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- CN1160210A CN1160210A CN 97100049 CN97100049A CN1160210A CN 1160210 A CN1160210 A CN 1160210A CN 97100049 CN97100049 CN 97100049 CN 97100049 A CN97100049 A CN 97100049A CN 1160210 A CN1160210 A CN 1160210A
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Abstract
Plural light emitting device groups are arranged in the direction perpendicular to the center line of a runway and each of them comprises plural light emitting devices different in light emitting angle from one another. A first controller controls said plural light emitting device groups so that light emitting devices having the same light emitting angle may emit light at the same time and light emitting devices having different light emitting angles may emit light one after another. Plural light receiving device groups are arranged, respectively, so as to correspond to the plural light emitting devices. A second controller controls said plural light receiving device groups so that light receiving devices which receive the reflected lights corresponding to the lights emitted from said light emitting devices having diferent situations. A detector outputs a passing detection signal to show that said flying object has passed said monitoring space when at least one of said plural light receiving devices has received a reflected light from said flying object.
Description
The present invention relates to (back is called monitored space and passes through sniffer) of the monitored space that a kind of survey mission object passed through, particularly a kind of monitored space of using when vectored flight object such as aircraft and similar aircraft lands is passed through sniffer, the monitored space that its survey mission object has passed through, and send the information detect to flyer.
In the approach and landing system of routine, GPS (after this being called GPS) receiver is used as a kind of Range Measurement System, as disclosed in day patented claim No.2-287900 of the present disclosure.This system makes aircraft can carry out the intricately approach, for example, utilize that microwave landing system (MLS) (back is called MLS) carries out that segmentation is marched into the arena, curved approach or other similar complicated approach, by using the range data of the precision that obtains from GPS (GPS) receiver.
With reference to Fig. 1, in the conventional Landing Guidance System of in day patented claim No.2-287900 of the present disclosure, announcing, the MLS signal that is received by antenna 71 is received processing by MLS receiver 72, and be transformed to parametric data as measurement of angle, in other words, be the position angle and the elevation angle, and the earth station antenna position, be delivered to navigational computer 73 then.
On the other hand, the gps signal that is received by gps antenna 77 is received processing by GPS receiver 76, and acceptance point, be that the aircraft position obtains measuring, and aircraft is to the distance of its landing point, be that the distance that calculates is used as range data and delivers to navigational computer 73 position data of measuring and calculating on the basis of the landing point position data on the runway of importing in advance.
Horizontal Situation Display (HSI) or can be used as navigation indicator 74 with the electronic horizon display (EHSI) that the ground diagram form shows.Under automatic driving condition, deviation data and range data that robot pilot 75 receives from navigational computer 73, and calculate aircraft and drive the control signal that rudder angle that control needs and control aileron need automatically.
In another conventional Landing Guidance System of in day patent No.5-72317 of the present disclosure, announcing, be with being arranged on the site error that GPS receiver in the ground system and calculation element calculate GPS, and this position error information is transmitted in the system in the aircraft by existing communication device.By the position error information of ground system emission, and by proofreading and correct the site error that the GPS receiver in the system obtains in machine, so that aircraft all can obtain range information accurately at any time.
With reference to Fig. 2, this conventional Landing Guidance System is made up of a ground system 80 and a mobile system 90.Ground system 80 is made up of a GPS receiver 81, a calculation element 82 and a microwave landing system (MLS) land station 83, and mobile system 90 is made up of a MLS antenna 91, a microwave landing system (MLS) receiver 92, a navigational computer 93, a navigation indicator 94, a robot pilot 95, a GPS receiver 96 and a gps antenna 97.
Obtain the position data of ground system 80 from the signal of gps satellite (draw and show explanation) by reception at the GPS on ground receiver 81.Calculation element 82 compares the physical location of position data with the ground system 80 that prestores, and the difference between them is sent to land station 83 as position error information.
This position error information is used as with latitude, longitude, height and similar parameters and is worth corresponding control information, and is converted into a specific format in MLS land station 83, as the MLS auxiliary data codes, launches in the scope of MLS territory then.
On the other hand, in mobile system 90, MLS receiver 92 is handled from ground system 80 emissions and the signal that received by MLS antenna 91, and the deviation information of reference azimuth is departed from the output position angle of receiving and the deviation information and the auxiliary data at the benchmark elevation angle are departed from the elevation angle of receiving.The deviation data and the auxiliary data of 92 outputs of MLS receiver are imported into navigational computer 93.And the position data of the expression aircraft self-position of being received by GPS receiver 96 by gps antenna 97 is also transported to navigational computer 93.The position data that GPS receivers 96 provide in the navigational computer 93 straightener loading systems 90 with a position error information, that is, and deviation information and auxiliary data, and export it self accurate aircraft position to navigation indicator 94.According to the data that send to robot pilot 95 by navigational computer 93, drive control automatically.In above-mentioned existing approach and landing system, by the MLS system that combines with the GPS receiver, make aircraft can carry out complicated approach, for example segmentation is marched into the arena, curved approach or other similar task.Compare with existing distance measuring equipment (DME) or precision distance measurement equipment (DME/P), GPS receiver range measurement accuracy is higher and cost is lower.
The landing flight path of the technical standard order aircraft of " International Civil Aviation Organization (ICAO) appendix 10 " should be set in the scope of overhead 15 meters to 18 meters of runway end points at present.
And the width that the course width of downward course is defined as on runway end points and the perpendicular aspect of runway centerline is 210 meters.That is to say, passed through 15～18 meters of the perpendicular width and 210 meter one space of horizontal plane width in the runway end points sky at aircraft after, aircraft rises its fuselage that has dived downwards and enters little head attitude of facing upward as horizontal landing or main landing gear landing.That is beginning landing flare operation.Therefore, the above-mentioned particular space of being made up of described vertical face width and described horizontal face width for entering the aircraft that last landing attitude will be judged the starting point of evening up operation, is a very important position, below this particular space is called monitored space.
Described in the above in Landing Guidance System by using GPS to come under the situation of detection monitored space, the positional precision that is obtained by the GPS receiver, non-encrypted and be tens meters when obtaining yard, under the situation of service precision or different GPS pattern, be several meters.
On the other hand, being ± 6 meters in the horizontal direction by the systematic error that the MLS receiver obtained, is ± 0.6 meter in vertical direction.In addition, the sum of errors apart from the ground surface height that obtains of the elevation data that is obtained by the MLS receiver self becomes several meters from the range data of the point that lands by what the GPS receiver obtained.Therefore, under the situation of only using GPS, it is needed at level and several centimetres of vertical direction or littler detection accuracy by particular space to obtain being used for hunter.
An object of the present invention is to provide a kind of sniffer that is used to monitor the monitored space of passing through, it is the particular space that passed through of survey mission thing at any time.
Another object of the present invention provides a kind of sniffer that is used to monitor the monitored space of passing through, and it is the particular space that passed through of survey mission thing at any time, and the spatial information that will pass through passes to aircraft.
In addition, another object of the present invention provides a kind of sniffer that is used to monitor the monitored space of passing through, and it can prevent the maloperation that caused by external disturbance when surveying the space that a flying object passed through.
For reaching each above-mentioned purpose, a kind of be used to monitor the sniffer by the space comprise a plurality of light emitting devices groups with a plurality of light emitting devices, light emitting devices is to be provided with in the direction perpendicular to runway centerline, and the light emission angle of each device differs from one another; One first controller, it is used to control described a plurality of light emitting devices group, so that be included in the light emitting devices that has the same light emission angle each other in described a plurality of light emitting devices group respectively, can launch light at one time, and make the light emitting devices that has different light emission angle each other that is included in respectively in described a plurality of light emitting devices group, can one by one launch light; A plurality of optical pickup apparatus groups, it is corresponding with a plurality of light emitting devices in being included in described a plurality of light emitting devices group to be provided with a plurality of optical pickup apparatus respectively, and when flying object when the predefined monitored space, optical pickup apparatus receive by the flying object reflection by the radiative reflected light of a plurality of described light emitting devices; One second controller, be used to control described a plurality of optical pickup apparatus group, can work simultaneously with the corresponding catoptrical optical pickup apparatus of light that the light emitting devices that has the same light emission angle is each other launched to be used in to receive, can work one by one with the corresponding catoptrical optical pickup apparatus of emission light of the light emitting devices of the light emission angle that differs from one another and be used in reception; And a detector that is used to export the detectable signal that passes through, when detectable signal has received reflected light at least one described optical pickup apparatus, described flying object is shown by described monitored space.
Above-mentioned or other purpose, feature and good effect of the present invention be by the detailed description below in conjunction with accompanying drawing, and being perfectly clear of becoming is clear.
Fig. 1 is the composition diagram of conventional landing system;
Fig. 2 is the composition diagram of another conventional landing system;
Fig. 3 is used to monitor a principle schematic by the sniffer in space according to the embodiment of the invention;
Fig. 4 is an embodiment of the invention synoptic diagram;
Fig. 5 is the skeleton view that embodiment of the invention light emitting devices group is provided with.
Fig. 6 is the sectional view that embodiment of the invention light emitting devices group is provided with;
Fig. 7 A is an expression aircraft when being in certain altitude, is used for the exploration operation figure of the embodiment of the invention of the monitored space that hunter passed through;
Fig. 7 B is an expression aircraft when being tending towards in the other direction, is used for the exploration operation figure of the embodiment of the invention of the monitored space that hunter passed through;
Fig. 7 C represents that aircraft is used for the exploration operation figure that hunter has passed through the embodiment of the invention of monitored space when being tending towards positive dirction.
Fig. 8 is the composition block scheme of pulse-modulator shown in the presentation graphs 3;
Fig. 9 is the composition block scheme of photoreceiver in the presentation graphs 3;
Figure 10 is according to another embodiment of the present invention, the example diagrammatic sketch of a monitored space of the setting of the sniffer that passes through by monitored space.
Various details one most preferred embodiment.
In this embodiment, each group in a plurality of light emitting devices groups comprises a plurality of light emitting devices with light emission angle Φ 1 to Φ n, so that from being limited to lower limit, intermittently or continuously cover predefined monitored space, comprise minimum approach altitude less so that cause on the airfield approach landing flight path, a plurality of light emitting devices groups are arranged on the direction perpendicular to the extended line of runway centerline.When the corresponding a plurality of optical pickup apparatus that are provided with a plurality of light emitting devices receive reflected light, these reflected light are at the reflected light that passes through on the airframe of the monitored space upper limit, some pulsed modulation light reflections that promptly are each a plurality of light emitting devices emissions with light emission angle Φ 1 provide, and these light emitting devices are to be included in respectively in a plurality of light emitting devices groups, at this moment increase with the output of receiving the photoreceiver that catoptrical optical pickup apparatus is corresponding., monitor that the output of a comparer of optical receiver output is reversed thereafter, ＂ or ＂ circuit according to different comparers outputs or, export a detectable signal has passed through monitored space with the expression aircraft the upper limit.
In an identical manner, when being arranged to corresponding with a plurality of light emitting devices a plurality of optical pickup apparatus and receiving reflected light, these reflected light are to be reflected on by the airframe of monitored space lower limit by some pulsed modulation light of the light emitting devices emission that respectively has light emission angle Φ n to provide, and these light emitting devices are to be included in respectively in a plurality of light emitting devices groups, and at this moment corresponding with receiving catoptrical optical pickup apparatus photoreceiver output increases.
, monitor that the comparer output of optical receiver output is reversed thereafter, one or circuit take out respective comparator output or, export a detectable signal with the expression aircraft lower limit by monitored space.
Light emission angle Φ 1 to Φ n sets with different value in advance, and this different value is to obtain by cutting apart the vertical width of monitored space from the upper limit to lower limit, so that it can not cause the omission of airplane sounding.Be set to light emission angle Φ 1 to Φ n owing to be included in the light emission angle of a plurality of light emitting devices in a plurality of light emitting devices groups, so can be with a suitable speed, from being limited to lower limit, with electrical method scanning monitoring space.
And the setting of optical pickup apparatus group is calculated with geometry, and preestablishes, thereby can not take place to survey omission for aircraft one acceptable deviation when aircraft landing is marched into the arena, and the approach deviation is stipulated in International Civil Aviation Organization's appendix 10.And adopt optical pickup apparatus, so that receive reflected light from the aircraft scattered reflection with wide beamwidth.
In addition, control these optical pickup apparatus, so that only have a pulse-modulator group and a reception of impulse unit, and be included in wherein pulse-modulator and the operation that can match mutually separately of pulse receiver, so that prevent the maloperation that causes by external disturbance light.Described result of detection, promptly survey the aircraft obtain the information of the upper limit by monitored space or lower limit be launched machine and be transmitted into aircraft at any time.
Therefore, an if particular space that constitutes by horizontal width and vertical width component, it comprises as minimum approach altitude (decision height), reference point, flare out altitude, the main positions that breaks away from deviation height and other similar data, it is set to a monitored space on the landing approach flight path, to monitor previously described parameter, and these particular spaces are interruptions or constitute continuously, be to launch a monitored space to aircraft at any time to pass through information so, and by GPS according to this information compensation three-dimensional measurement precision, therefore, under the very poor situation of weather, can finish high-grade landing with the GPS method.Here, reference point refers to the point of a certain height [15 meters (50 feet)+3 meters (10 feet)] that is positioned on runway centerline and the critical line point of crossing, and the straight line portion of the downward extension of instrument landing system (ILS) landing flight path passes through this point.Even up and refer to when landing prow and be the operation of the fuselage pull-up of the attitude that has a down dip, and slightly be the prow attitude that makes progress when body horizontal landing or main landing gear are contacted to earth.The height that begins this operation is known as evens up starting altitude.Break away from biased operation and refer at aircraft and prepare having when landing under the crosswind condition, though aircraft continues normally to descend, and keep the aircraft prow, a driver behavior of just line up with runway direction of operating aircraft prow before landing in face of wind.And the height that begins this operation is called as and breaks away from the deviation starting altitude.
Below in conjunction with accompanying drawing, what describe the embodiment of the invention in detail is used to monitor sniffer by the space.
Arrive Fig. 6 with reference to Fig. 3, this embodiment to be used for the sniffer that monitored space passes through be by a pulse producer 1, one comprises the switch 2 of a plurality of gate circuit 2a--2n, one comprises the pulse-modulator 3 of a plurality of pulse-modulator 3a--3n, one comprises the optical sender 4 of a plurality of light emitting devices group 4a--4n, one comprises the photoreceiver 5 of a plurality of optical pickup apparatus group 5a--5n, one comprises the optical receiver 6 of a plurality of optical receiver 6a--6n, one comprises the detector 7 of a plurality of OR circuit 7a--7n, a scanning monitor 8, and one comprise transmitter 9 and 10 the transmitter of bursting at the seams constitutes.
As shown in Figure 3, a monitored space E has a upper limit that is limited by cut-off rule AB and the lower limit that is limited by cut-off rule CD.And the size of monitored space E is limited by horizontal width W and vertical width HO.
On the light emitting devices group 4a to 4n of transmitter 4 is set at direction perpendicular to extended runway centerline, and be to be set on the position that precomputes, so that they at the upper limit A-B of monitored space E (cut-off rule AB) to the scope between lower limit C-D (cut-off rule CD), can have the light emission angle of Φ 1--Φ n.As shown in Figure 3, a plurality of light emitting devices 4a-i (i=1,2,, m-1 m) is set at the position that precomputes, so that they can have the smooth emission angle Φ 1 at the upper limit A-B of monitored space E, as shown in Figure 4, a plurality of light emitting devices 4n-i are set on the position that precomputes, so that they can have the light emission angle Φ n at the lower limit C-D of monitored space E.As shown in Fig. 5 and Fig. 6, the light emitting devices group 4--i of optical sender 4 has a smooth emission array modular structure, and wherein light emitting devices 4a-i to 4n-1 is provided with the form of array.That is to say that light emitting devices 4a-i is set in advance to the optical axis that makes it can form a smooth emission angle Φ 1, and light emitting devices 4n-i is set in advance to the optical axis that makes it and can forms a smooth emission angle Φ n.Light emission angle Φ 1 is an angle of setting for the upper limit A-B of electronics method scanning monitoring space E, and light emission angle Φ n is an angle of setting for the lower limit C-D of electronics method scanning monitoring space E.The light emitting devices group 4-i of one modular structure is perpendicular to the center line of runway 11, and is arranged on the ground surface with proper spacing.For example, light emitting devices group 4-i is the end points portion that is embedded in runway 11, just in the critical line.
Though under desired perfect condition, the interval d1 of Y direction is 0 between the light emitting devices 4a-i that is provided with in a plurality of light emitting devices group 4-i, but in fact this be at interval the minimum aircraft that in monitored space E, will survey span width W S about 1/10.Interval d1 between a plurality of light emitting devices 4a-i represents by following formula:
d1＝H1×tanΦ1
Here H1 is the maximum height of monitored space E, just Gao Du the upper limit.
Same reason, though under desirable needed state, the interval dn of Y direction is 0 between the light emitting devices 4n-i that is provided with in many light emitting devices group 4-i, but in fact this be at interval the minimum aircraft that in monitored space E, will survey span width W S about 1/10.Interval dn between a plurality of light emitting devices 4n-i represents by following formula:
dn＝Hn×tanΦn
Here Hn is the minimum constructive height of monitored space E, just Gao Du lower limit.
Though under desirable required state, in light emitting devices group 4-i between the light emitting devices, for example between the light emitting devices 4a-1 and 4b-1 in light emission group 4-1, between light emitting devices 4b-1 and the 4c-1 ... or 4 between (n-1)-1 and the 4n-1, Y-axis to interval delta d be 0, in fact this at interval will be with about 1/10 of the minimum aircraft vertical width TS that is detected in monitored space E.
A plurality of pulse-modulator 3a-3n of pulse-modulator 3 carry out a control automatically, so that make the output of optical sender 4 can keep constant and generation synchronizing pulse 101a-101n.A plurality of pulse-modulator 3a-3n are made up of a plurality of pulse-modulator 3a-i-3n-i respectively, and pulse-modulator 3a-i-3n-i is corresponding to corresponding light emitting devices 4a-i-4n-i, and pulse-modulator 3a-i-3n-i produces synchronizing pulse 101a-i-101n-i respectively.
A plurality of gate circuit 2a-2n of switch 2 lead to-break control to the input signal of the pulse-modulator 3a-3n of AND circuit correspondence respectively.A plurality of gate circuit 2a-2n are made of the gate circuit 2a-i-2n-i that corresponds respectively to light emitting devices 4a-i-4n-i.
The pulse input signal 100a--100n that pulse producer 1 has nothing in common with each other frequency adds to a plurality of gate circuit 2a-2n of switch 2 respectively.Door scanning monitor 8 outputs to door scan control signal 104a-104n respectively a plurality of gate circuit 2a-2n of switch 2, so that from the light emitting devices 4a-i-4n-i of optical sender 4 to the upper limit A-B of the monitored space E space to the lower limit C-D scope, with suitable speed with electronics method scanning output.
Under the situation of the receivable deviation ± Φ 1 that considers aircraft 12 in advance, a plurality of optical pickup apparatus group 5a-5n of photoreceiver 5 are positioned in perpendicular on the direction on the extended line of runway 11 center lines, so that receive the dispersion reflected light 103a-103n by the aircraft of monitored space E effectively.A plurality of optical pickup apparatus group 5a-5n are made up of the optical pickup apparatus 5a-i-5n-i that corresponds respectively to light emitting devices 4a-i-4n-i respectively.
A plurality of photoreceiver 6a-6n of photoreceiver 6, the electric current-voltage transformation by the output to a plurality of optical pickup apparatus 5a-5n is carried out amplifies, the comparison of signal after filtering separation, rectification, shaping and the conversion then, obtains numeral output.A plurality of photoreceiver 6a-6n are made up of the photoreceiver 6a-i-6n-i that corresponds respectively to optical pickup apparatus 5a-i-5n-i respectively.
When at least one had been changed in the output of a plurality of photoreceiver 6a-6n, a plurality of OR circuit 7a-7n of detector 7 were used to show that to transmitter 9 outputs aircraft 12 has passed through the detectable signal 105a-105n of monitored space E.
On the basis from the detectable signal 105a-105n of a plurality of OR circuit 7a-7n respectively, transmitter 9 passes through information by antenna 10 to aircraft 12 emission monitored space E.
Describe below use Fig. 3-embodiment illustrated in fig. 6 device be used for the detection method that monitored space is passed through.
At first, pulse producer 1 produces the pulse input signal 100a-100n that frequency has nothing in common with each other, and exports pulse input signal 100a-100n respectively to a plurality of gate circuit 2a-2n.A plurality of gate circuit 2a-2n are subjected to the control from the door scan control signal 104a-104n of door scanning monitor 8, so that at interval according to the suitable classification that calculates with the size of aircraft 12 in advance, the lower limit C-D scanning monitoring space E from the upper limit A-B of monitored space E to it.That is to say, a plurality of gate circuit 2a-2n are subjected to the control from the door scan control signal 104a-104n of door scanning monitor 8, so that export pulse input signal 100a-100n from pulse generator 1 respectively to multiple-pulse modulator 3a-3n at interval with suitable classification.
A plurality of pulse-modulator 3a-3n with suitable classification at interval, with pulse input signal from pulse producer 1 from a plurality of gate circuit 2a-2n inputs, a plurality of light emitting devices group 4a--4n that pulsed drive is corresponding with them, and to the photoreceiver 6a-6n of correspondence transmission synchronizing pulse 101a-101n.Therefore, the light emitting devices that has the same light emission angle each other in a plurality of light emitting devices 4a-4n is Be Controlled respectively, so that they launch light at one time, and the light emitting devices with the light emission angle that differs from one another in a plurality of different light emitting devices group 4a-4n, thereby Be Controlled is launched light seriatim respectively.
The maloperation that causes by external disturbance light, can pass through gating pulse modulator and photoreceiver, so that prevented by the pulse-modulator of pairing each other and the operation of optical receiver, for example, a pair of pulse-modulator 3a and optical receiver 6a are only arranged, a pair of pulse-modulator 3b and optical receiver 6b ... and a pair of pulse-modulator 3n and optical receiver 6n can be operated.
The output of a plurality of pulse-modulator 3a-3n is transmitted into the monitored space E to lower limit C-D scope from upper limit A-B by light emitting devices group 4a-4n by with suitable sweep velocity and suitable sweep segment.
A plurality of light emitting devices group 4a-4n and a plurality of optical pickup apparatus group 5a-5n are set on the center line extended line direction perpendicular to runway 11, and be set at the position that precomputes, so that the light emission angle of light emitting devices group 4a-4n and the incident angle on aircraft 12 and reflection angle can be respectively Φ 1 ... Φ n.For example, as shown in Figure 3, come the upper limit A-B of monitored space E when aircraft 12, from the light modulated among the pulsed modulation light 102a of light emitting devices 4a, be that a light modulated among the pulsed modulation light 102a-1-102a-m reflects on aircraft 12, and receive reflected light 103a by corresponding optical pickup apparatus group 5a.The output of this optical pickup apparatus group 5a is imported into corresponding optical receiver 6a.In the same way, for example as shown in Figure 4, come the lower limit C-D of monitored space E when aircraft 12, from the light modulated among the pulsed modulation light 102n of light emitting devices group 4n, be that a light modulated among the pulsed modulation light 102n-1-102n-m reflects aboard, and receive reflected light 103n by corresponding optical pickup apparatus group 5n.The output of this optical pickup apparatus 5n is imported into corresponding optical receiver 6n.In this method, the output of a plurality of optical receiver 6a-6n is imported into OR circuit 7a-7n, and can access the detectable signal 105a-105n that expression aircraft 12 has passed through monitored space.
With reference to Fig. 7 A-7C exploration operation that the monitored space that is used for the sniffer that monitored space passes through of this embodiment passes through and the relation between the receivable deviation of aircraft are described below.
With reference to Fig. 7 A, be in when aircraft 12 under the situation of a certain height, the light emission angle of light emitting devices 4a-1 emission is that the pulsed modulation light 102a-1 of Φ 1 is mapped on the aircraft 12 with incident angle Φ 1, and reflected by aircraft 12 with reflection angle Φ 1, reflected light 103a from aircraft 12 is received by optical pickup apparatus 5a-1, and this optical pickup apparatus 5a-1 is close from the vertical axis of aircraft 12 and a bit of runway 11 point of crossing one segment distance 11.
With reference to Fig. 7 B, aircraft 12 with reverse angle Δ light modulated 1 an inclination situation under, only be mapped on the aircraft 12 from the pulsed modulation of the light emission angle Φ 1 of light emitting devices 4a-1 emission, and reflected by aircraft 12 with reflection angle Φ 1+ Φ 1 with incident angle Φ 1+ ΔΦ 1.Reflected light 103a from aircraft 12 is received by optical pickup apparatus 5a-1, this optical pickup apparatus 5a-1 close from aircraft 12 vertical axis and runway 11 intersection be H1 * tan (Φ 1+2 ΔΦ 1) a bit.
With reference to Fig. 7 C, under the angle ΔΦ 1 inclination situation of aircraft 12, only be mapped on the aircraft 12 from the pulsed modulation of the light emission angle Φ 1 of light emitting devices 4a-1 emission, and reflected by aircraft 12 with reflection angle Φ 1-ΔΦ 11 with incident angle Φ 1-ΔΦ 1 with a forward.Reflected light 103a from aircraft 12 is received by optical pickup apparatus 5a-1, this optical pickup apparatus 5a-1 close from aircraft 12 vertical axis and runway 11 intersection be H1 * tan (Φ 1-2 ΔΦ 1) a bit.
About the acceptable pitch angle of aircraft 12, in the standard of International Civil Aviation Organization's appendix 10 and the supervision rules of flying, be defined as in ± 20 degree scopes.
Below with reference to Fig. 8 the pulse-modulator that present embodiment is used for the sniffer that monitored space passes through is illustrated.
With reference to Fig. 8, pulse-modulator 3a-1 comprises an on-off circuit 30a-1, the optical pickup apparatus 31a-1 of an interior dress, one impact damper 32a-1, one peak holding circuit 33a-1, a reference voltage 34a-1, a differential amplifier 35a-1 and a light emitting devices driving circuit 36a-1.
The pulse input signal 100a that is produced by pulse producer 1 is input to the on-off circuit 30a-1 that is used for light emitting devices 4a-1 by gate circuit 2a-1, and light emitting devices 4a-1 is made of laser diode or similar device.On-off circuit 30a-1 is switched on or switched off light reflecting device 4a-1 according to the pulse input signal 100a of input.As light emitting devices 4a-1 during in on-state, after built in light receiving trap 31a-1 will be converted to an electric signal from the signal photoelectricity ground for light signal of light emitting devices 4a-1 output, peak holding circuit 33a-1 was by the peak level of impact damper 32a-1 acquisition.
Peak level that differential amplifier 35a-1 keeps with peak holding circuit 33a-1 and predefined reference voltage 34a-1 be as input, and export the input signal of their difference output as light emitting devices driving circuit 36a-1.
Form owing to have circuit recited above, when light emitting devices group 4a-4n connected, system always was subjected to a feedback, made the light of light emitting devices group 4a-4n emission be stabilized in a level.Other pulse-modulator 3a-2-3a-m ..., 3n-1---3n-m also has the identical structure with described pulse-modulator 3a-1, and with the method work identical with pulse-modulator 3a-1.
Below with reference to Fig. 9 the monitored space of this embodiment is illustrated by the optical receiver in the sniffer.
With reference to Fig. 9, optical receiver 6a-1 comprises an amplifier 61a-1, a bandpass filter 62a-1, a gate circuit 63a-1, a rectifier 64a-1, a shaping circuit 65a-1 and a comparer 66a-1.
Through rectifier 64a-1 full-wave rectification, shaping circuit 65a-1 shaping is transformed to numeral output 106a-1 by comparer 66a-1 then from the signal of door 63a-1 output.
Other optical receiver 6a-1-6a-m ..., 6n-1-6n-m also has the identical structure with described optical receiver 6a-1, and works in the mode identical with described optical receiver 6a-1.
Below in conjunction with Figure 10,, be illustrated in particular for the example of monitored space to the sniffer that monitored space is passed through that is used for of another embodiment of the present invention.
With reference to Figure 10, on last landing passage, show the glide paths 22 and the ideal track 23 of aircraft wheel.On glide paths 22, show according to existing ILS or microwave landing system (MLS) and be used to decision height category I (=60 meters) 20a that marches into the arena and land required, judgement height category II (=30 a meters) 20b, and a reference point (=15 meters+3-0 rice) 20C.
Here, decision height refers to the minimum altitude that can drop to instrument flight when carrying out Precision Approach landing, is the continuation final landing and obtains the needed minimum altitude of essential instruction.The minimum altitude that decision height category I refers to is equal to or higher than 60 meters (200 feet), and the minimum altitude that decision height category II refers to is equal to or higher than 30 meters, and is lower than 60 meters.
Under the situation of decision height category I, the pilot must have 60 meters or be higher than on 60 meters the height and with the naked eye discern runway 11 from runway 11, if the pilot can not with the naked eye discern it, the pilot will abandon landing.Under the situation of decision height category II, the pilot must have 30 meters or be higher than 30 meters from runway 11, and is lower than on 60 meters the height and with the naked eye discerns runway 11, if the pilot can not with the naked eye discern it, the pilot abandons landing.
Theoretical ideal trajectory 23 shows the instrument landing track of existing jet plane, on track 23, show one and even up judgement height (=22.5 meters) 20d, one evens up beginning height (=9 meters) 20e, and one breaks away from deflection begins height (=6 meters) 20f, and the main landing gear point 20g that lands.
The sniffer that monitored space passes through that is used for by this embodiment is respectively above-mentioned height setting monitored space 28a-28f, and for those monitored space 28a-28f the sniffer that monitored space is passed through that is used for described above is set respectively.The extended line of reference numerals 27 expression runways 11 center lines.
Here, be set to the course width 24 of directional beacon regulation in existing ILS at the horizontal width of decision height category I monitored space 28a, and be set in 15 meters+3 to-0 meter in the vertical width of reference point 20C monitored space 28C.
The horizontal width 26 of monitored space 28C is 210 meters (700 feet).Monitored space 28d relevant with another flare control and the horizontal width of 28f are set to course width 24 and are complementary, and the vertical width of monitored space 28d and 28f is set at a suitable width.
Though example provides in Figure 10 is in the end to land in the flight path, on main positions, be interrupted the monitored space 28a-28f that is provided with, if in the end land in the flight path, monitored space is set continuously comprising on the continuous position of main positions, so also surveillance aircraft 12 passes through monitored space continuously.
In such method, a plurality of light emitting devices group 4a-4n and a plurality of optical pickup apparatus group 5a-5n that correspond respectively to a plurality of light emitting devices group 4a-4n are set on that precompute and extended line 27 vertical direction runway 11 center lines 21, so that the reflection angle of the angle of light of the light emission angle of a plurality of light emitting devices group 4a-4n and aircraft 12 and aircraft 12 can be respectively Φ 1-Φ n.The a plurality of optical receiver 6a-6n that correspond respectively to a plurality of optical pickup apparatus group 5a-5n are that output with a plurality of optical pickup apparatus 5a-5n is as input, and to the OR circuit 7a-7n output digital signal that corresponds respectively to a plurality of optical receiver 6a-6n.
When at least one was changed in the output of a plurality of optical receiver 6a-6n, expression aircraft 12 outputed to transmitter 9 by the detectable signal 105a-105n of a monitored space from a plurality of OR circuit 7a-7n that correspond respectively to photoreceiver device group 5a-5n.Transmitter 9 passes through information to aircraft 12 emissions based on the monitored space of these detectable signals 105a-105n, can be interrupted or form monitored space 28a-28f continuously, monitored space 28a-28f is included in the main positions in the approach track, as minimum approach height (decision height: decision height category I20a and decision height category II20b), reference point 20C, flare out altitude and disengaging deflection height, at any time the monitored space 28a-28f that passes through of hunter 12, and can close 12 emissions to aircraft and pass through information.
Owing to the monitored space 28a-28f that can be interrupted or formation is included in the main positions in the approach track continuously, can pass through information to aircraft emission monitored space at any time, so by GPS according to that information compensation three-dimensional measurement precision, under the situation of weather difference, can finish high-grade landing with GPS.
In the case, because a plurality of light emitting devices group 4a-4n of pairing and a plurality of optical pickup apparatus group 5a-5n are respectively mutually by synchronously driven mutually, in having light emission angle Φ 1-Φ n scope among a plurality of light emitting devices 4a-i-4n-i of same light emission angle each is right, use and other each pulsed modulation light, so they are subjected to the external world dried very little according to the influence of light different frequency.
Because the pulsed modulation light 102a-102n that has surveyed from a plurality of light emitting devices group 4a-4n emissions reflects the reflected light 103a-103n that provides on aircraft 12, whether this detection is to have an input signal to enter a plurality of optical pickup apparatus group 5a-5n, a plurality of optical pickup apparatus group 5a-5n are arranged on the direction perpendicular to the extended line 27 of runway 11 center lines 21, so that each in them can also can be matched with a symmetry among a plurality of light emitting devices group 4a-4n, so vertical stratification is unnecessary, and it can satisfy landing area easily, it is surperficial to land, transition face and the similarly different requirements of prescribed condition in International Civil Aviation appendix 10.
In addition, to approach and landing system,, can pass through the precision of information compensation three-dimensional measurement according to this by enough GPS, and can under bad weather, finish high-grade landing by GPS by using the monitored space of the present invention that combines with GPS by sniffer.
Claims (15)
1. one kind is used for the survey mission object by the device of monitored space, and it comprises: a plurality of light emitting devices groups, light emitting devices group comprise a plurality of light emitting devices that are provided with on aspect runway centerline is vertical, and their light emission angle has nothing in common with each other;
One first controller, be used to control described a plurality of light emitting devices group, so that be included in light emitting devices in described a plurality of light emitting devices group respectively with same light emission angle, can launch light at one time, and the light emitting devices with the emission angle of not sharing the same light that is included in respectively in described a plurality of light emission group can be launched light seriatim;
A plurality of optical pickup apparatus groups, the optical pickup apparatus group comprises a plurality of optical pickup apparatus, a plurality of optical pickup apparatus are separately positioned on and are included in a plurality of light emissions respectively and organize described light emitting devices opposite position, and the light that is received from described a plurality of light emitting devices emissions is by the reflected light on the flyer of a predefined monitored space;
One second controller, be used to control described a plurality of optical pickup apparatus group, so that receive corresponding to can being simultaneously operated from the radiative reflected light optical pickup apparatus of the light emitting devices with same light emission angle, and receive corresponding to can operating one by one from the radiative reflected light optical pickup apparatus of the light emitting devices with the emission angle of not sharing the same light;
And a detector that is used to export by detectable signal, when detectable signal has received reflected light at least one described a plurality of optical pickup apparatus, the described monitored space that described flyer has passed through is shown.
2. device according to claim 1 is characterized in that also comprising:
Be used for launching a described transmitter of described detector output by detectable signal to described flyer.
3. device according to claim 1, it is characterized in that: each the described optical pickup apparatus that is included in each described a plurality of optical pickup apparatus group is arranged on such position, when described flyer by in described monitored space during a privileged site, on described flyer, reflect the reflected light that obtains at the light that it only can be received from corresponding to a light emitting devices emission of described optical pickup apparatus on this position.
4. device according to claim 1 is characterized in that: described first controller is controlled described a plurality of light emitting devices, so that vertically scan described monitored space from described monitored space upper limit height to the lower limit height.
5. device according to claim 4, it is characterized in that: when scanning described monitored space from being limited to lower limit with described a plurality of light emitting devices, corresponding to of the control of described first controller to described light emitting devices, described second controller is controlled described a plurality of optical pickup apparatus, so that the reflected light when receiving from described flyer by described monitored space.
6. will show 1 described device according to right, it is characterized in that: described monitored space is to be interrupted setting in advance, so that comprise minimum approach altitude at least on the approach track of described flyer.
7. device according to claim 1 is characterized in that: described monitored space is to be provided with continuously in advance, so that comprise minimum approach altitude at least on the approach track of described descending object.
8. according to claim 1, device is characterized in that: described monitored space is set, so that comprise that on the approach track of described flyer minimum approach altitude, a reference point, a hand-pulled noodles begin height and and break away to tilt the beginning height.
9. device according to claim 1 is characterized in that: described a plurality of light emitting devices are with predetermined being disposed on the ground.
10. device according to claim 1 is characterized in that: be included in the light emitting devices that has the same light emission angle each other in described a plurality of light emitting devices respectively and be with detectable minimum flyer and be provided with at about 1/10 interval of width on the direction that light emitting devices is provided with.
11. device according to claim 1 is characterized in that: the described light emitting devices that is included in a setting adjacent one another are in the described light emitting devices group is to be provided with at about 1/10 interval of width on perpendicular to the direction on ground with detectable minimum flying object.
12. device according to claim 4 is characterized in that described first controller comprises:
One is used for the pulse producer of output pulse signal;
A plurality of pulse-modulators are set to correspond respectively to a plurality of light emitting devices, and drive the light emitting devices of described correspondence;
A plurality of conversion switch circuits, be set to correspond respectively to described a plurality of pulse-modulator, and carry described pulse signal to the pulse-modulator of described correspondence at interval with predefined classification, so that described a plurality of light emitting devices can scan described monitored space to the lower limit height from upper limit height.
13. device according to claim 12 is characterized in that described each pulse-modulator comprises:
One on-off circuit, it is on the basis of the pulse signal of described conversion switch circuit output, and switch is controlled corresponding light emitting devices;
One feedback control circuit, it with the emission light of described light emitting devices output as an input optical signal, and on the basis of this optical signalling signal level the output level of the described optical launcher of control.
14. device according to claim 12 is characterized in that described second controller comprises:
A plurality of optical receivers, they correspond respectively to described a plurality of pulse-modulator setting, and with electric current-voltage transitions that the pulse signal of described pulse-modulator output synchronously carries out the output of described corresponding light receiving trap, export digital signal then;
One OR circuit is used for according to exporting the survey mission object by described monitored space from least one of described a plurality of optical receivers.
15. device according to claim 14 is characterized in that described optical receiver comprises:
An amplifier, it carries out the electric current-voltage transitions from described corresponding light receiving trap output, then the signal level after the conversion is amplified to a level that needs;
One bandpass filter of separating the signal after described amplifier amplifies from frequency;
One gate circuit is used for synchronously exporting the signal of exporting from described bandpass filter with the pulse signal of described corresponding pulses modulator output;
One is used for the rectification circuit of the described gate circuit output signal of full-wave rectification;
One is used for the waveform shaping circuit of the shaping of signal after the described rectification circuit full-wave rectification;
One change-over circuit is used for conversion of signals after the shaping being become a digital signal and it being exported.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2221996A JPH09214751A (en) | 1996-02-08 | 1996-02-08 | Facsimile equipment providing picture reduction function |
| JP40222/1996 | 1996-02-28 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1160210A true CN1160210A (en) | 1997-09-24 |
Family
ID=12076698
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 97100049 Pending CN1160210A (en) | 1996-02-08 | 1997-02-28 | Apparatus for detecting that flying object has passed monitoring space |
Country Status (2)
| Country | Link |
|---|---|
| JP (1) | JPH09214751A (en) |
| CN (1) | CN1160210A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100365428C (en) * | 2003-07-03 | 2008-01-30 | 夏普株式会社 | Humanbody detecting apparatus and electronic machine matched with the same |
| CN101819490A (en) * | 2009-02-27 | 2010-09-01 | 索尼公司 | Reflection detection apparatus, display apparatus, electronic apparatus, and reflection detection method |
-
1996
- 1996-02-08 JP JP2221996A patent/JPH09214751A/en not_active Withdrawn
-
1997
- 1997-02-28 CN CN 97100049 patent/CN1160210A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100365428C (en) * | 2003-07-03 | 2008-01-30 | 夏普株式会社 | Humanbody detecting apparatus and electronic machine matched with the same |
| CN101819490A (en) * | 2009-02-27 | 2010-09-01 | 索尼公司 | Reflection detection apparatus, display apparatus, electronic apparatus, and reflection detection method |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH09214751A (en) | 1997-08-15 |
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