CN207321264U - One kind is used for Aircraft Vectoring System device for fast detecting - Google Patents

Abstract

The utility model discloses one kind and is used for Aircraft Vectoring System device for fast detecting, including the hollow body for mutually fastening and being formed, radio frequency component, control assembly, power supply module are provided with the body cavity body, surface is provided with display, and is electrically connected between the radio frequency component, control assembly, power supply module, display；The side of the body is provided with guidewire lumen.The purpose of this utility model is to provide one kind and is used for Aircraft Vectoring System device for fast detecting, and portable convenient, can realize that outfield is independently detected, for former seat in the plane detection and maintaining unit Aircraft Vectoring System original seat in the plane factory testing before taking off to Aircraft Vectoring System.

Description

One kind is used for Aircraft Vectoring System device for fast detecting

Technical field

The utility model belongs to detection device, is specially that one kind is used for Aircraft Vectoring System device for fast detecting, for the people Navigate aircraft, aircraft of opening the navigation or air flight, military aircraft navigation system former seat in the plane detection and maintaining unit Aircraft Vectoring System original seat in the plane before taking off Factory testing.

Background technology

Navigation signal simulator includes four patterns, i.e.,：（Course）LOC patterns,（Glide）GS patterns,（Nodirectional beacon） VOR patterns,（Marker beacon）MKR patterns, can virtual airport completely instrument-landing-system（Instrument Landing System, ILS）It is most widely used aircraft precision approach guidance system.Its effect is built with radio signal Vertical one is directed toward aerial narrow " tunnel " by runway, and aircraft determines itself phase with " tunnel " by airborne ILS receiving devices To position, as long as aircraft is maintained at the flight of " tunnel " center, so that it may fly nearly runway, smoothly falling head along correct direction, most Runway is flown into eventually and is landed.

（Course）LOC patterns：That is Localizer, abridge LOC, it provides the signal being aligned with runway centerline or so.Hair Penetrate machine be installed on runway distal end, the radio signal sent is high directivity, by runway distal end, in sector be directed toward run Road entrance（Near-end）Direction, and come to aircraft to extension.More remote from runway, the scope that sector carries out lid is bigger.Signal is being run The representative width of road inlet is 700 feet（213 meters）, locate in the sea from runway threshold 4-7, signal is carried out lid scope and expanded to 2000-3000 feet.In general, aircraft is located in the range of 35 degree of runway extended line drift angle（That is 70 degree of fan shape center angle）When, Effective LOC signals can be received（LOC gauge pointers in cockpit are within completely inclined scope）.

（Glide）GS patterns：That is Glide Slope, abbreviation GS it the route of aircraft falling head is defined in vertical direction. Transmitting antenna is installed on beside runway, from runway threshold（Near-end）About 1000 feet（305 meters）.Signal center's line and runway plane Formed inclination angle is generally 3 degree, and G/S signal scope has certain " thickness ", the fan shape center angle of G/S signal in vertical direction About 1.4 degree.1 mile from antenna（About 1.6 kilometers）Place, G/S signal are about 140 feet thick.That is, fly to 1 mile from antenna When, if aircraft altitude and signal center's line deviation are more than 70 feet, it just can not receive effective G/S signal（GS in cockpit refers to Pin is beyond completely inclined scope）.

（Marker beacon）MKR patterns：That is marker beacons.Aircraft come to runway extended line on be separated by a spacing From be provided with three vertically upward launch signal low power beacon radio station, when aircraft beacon overhead by when, be received by Signal, the beacon ray light in cockpit are just lighted, and with the audio signal of Morse code.Pilot can judge aircraft with running accordingly The substantially relative position in road.But some ILS are only equipped with two beacons, i.e. OM and MM long distances beacon：Outer marker, abbreviation OM, also referred to as far from the table or outside finger.During by OM overhead, the OM signal lamps in cockpit（Blueness）Light, Morse code sound is " it is long, it is long, long ".OM is typically the position of aircraft incision electronics glide path GS, and during by OM overhead, the GS pointers in cockpit should In middle position.In typical case, aircraft altitude is about 2500-4000 feet of AGL at this time, and OM is apart from runway threshold about 7- 10 nautical miles.Middle-range beacon, i.e. middle marker, abridge MM, also referred to as middle platform or middle finger.During by MM overhead, in cockpit MM signal lamps（It is amber）Light, Morse code sound is " short, long, short, length ".MM is built in from 3500 English of runway threshold Ruler（1067 meters）Place, since GS is typically all 3 degree, it can be calculated that aircraft and the relative height differential of runway access area at this time For 200 feet（61 meters）Low coverage beacon, i.e. inner marker, abridge IM, also referred to as close-table or interior finger.During by IM overhead, IM signal lamps in cockpit（White）Light, Morse code sound is " short, short, short, short ".

（Nodirectional beacon）VOR patterns：VHF Omnidirection range (VHF Omni-directional Range, it is simple below Claim VOR), it is a kind of radio navigation system for aviation, the signal that VOR transmitters are sent has two：One is that phase is consolidated Fixed reference signal；The phase of another signal is consecutive variations with the circumferential angle around beacon station, that is to say, that each The phase of the signal of a angle transmitting is all different.What it is to 360 degree (direction magnetic north pole) transmitting is same phase with reference signal （Phase difference is 0）, and the signal and reference signal phase difference 180 degree launched to 180 degree (direction south magnetic pole).VOR on aircraft Receiver according to the phase differences of received two signals can calculate and itself be in beacon station and launch to which angle Signal on, that is to say, that VOR systems determine that aircraft orientation in the air, it determines orientation VOR usually and rangefinder (Distance Measuring Equipment, DME) is installed with location, while aircraft directional information is supplied to, moreover it is possible to Aircraft is provided to the range information of guidance station, the orientation of such aircraft can be uniquely determined.

In the prior art, interior field detecting is usually used in the detection to Aircraft Vectoring System signal, i.e., is needed in aircraft It is detected in specified field, it is necessary to dismantle part, then individually detect, process is cumbersome, and can not complete independently to detect.For Problem above, there is provided one kind is used for Aircraft Vectoring System device for fast detecting, and portable convenient, can realize that outfield is independently detected, The device can be detected according to type of airplane in cabin or outside cabin；At the same time in order to overcome detection in, it is necessary to often into Row charging, cable holder is more inconvenient, is equipped with guidewire lumen.

Utility model content

The purpose of this utility model be in view of the above problems, provide one kind be used for Aircraft Vectoring System device for fast detecting, Portable convenient, can realize that outfield is independently detected, and fly for former seat in the plane detection and maintaining unit before taking off to Aircraft Vectoring System Machine navigation system original seat in the plane factory testing.

In order to achieve the above object, the technical solution adopted in the utility model is：One kind is quickly examined for Aircraft Vectoring System Survey device, including the hollow body for mutually fastening and being formed（1）, the body（1）Radio frequency component, control group are provided with cavity Part, power supply module, surface is provided with display, and is electrically connected between the radio frequency component, control assembly, power supply module, display Connect；The body（1）Side be provided with guidewire lumen（2）.

Further, the guidewire lumen（2）For hollow cavity, pass through dovetail slide（201）With body（1）Connection；It is oriented to Chamber（2）Lower part is provided with guide rail（24）, guide rail stage casing is provided with fixed seat（23）, fixed seat（23）Both sides are provided with sliding seat （22）；The sliding seat（22）On be provided with wire box（21）；Wire box（21）Bottom is provided with sliding slot（210）, sliding slot（210）Inside set It is equipped with and sliding block（211）；Sliding block（211）Upper surface is provided with wrapping post（212）, lower section is provided with sleeve（213）；The slip Seat（22）It is provided with and sleeve（213）The boss of cooperation（221）.

Further, the fixed seat（23）With sliding seat（22）Between be provided with flexible restoring organ.

Further, the flexible restoring organ includes being arranged at fixed seat（23）With sliding seat（22）Between spring （25）, sliding seat（22）Towards fixed seat（23）Bayonet lock is provided with end face（222）, fixed seat（23）Corresponding end-faces are provided with Pin hole（232）；Pin hole（232）Bottom is provided with elastic clamping block（233）, elastic clamping block（233）Lower part is provided with elastic component （234）, top is provided with the lockhole with exterior perforation（231）.

Further, wire box（21）Bottom is provided with and lockhole（231）Matched lock pin（213）.

The beneficial effects of the utility model：

1st, portable convenient, can realize that outfield is independently detected, the device can according to type of airplane, in cabin or Detected outside cabin；

2nd, guidewire lumen is provided with, facilitates charging wire to store；Flexible restoring organ make it that take-up is quick and convenient.

Brief description of the drawings

Fig. 1 is the utility model dimensional structure diagram.

Fig. 2 regards schematic diagram for the utility model wire box structure.

Fig. 3 is the utility model wire box schematic top plan view.

Fig. 4 is the utility model wire box schematic front view.

Fig. 5 is the utility model fixed seat structure schematic diagram.

Fig. 6 is structure diagram at B in Fig. 2.

Label character is expressed as described in figure：1st, body；2nd, guidewire lumen；11st, antenna；201st, dovetail slide；20th, charge Line；21st, wire box；22nd, sliding seat；23rd, fixed seat；24th, guide rail；25th, spring；210th, sliding slot；211st, sliding block；212nd, wrapping post； 213rd, sleeve；221st, boss；222nd, bayonet lock；231st, lockhole；232nd, pin hole；233rd, elastic clamping block；234th, elastic component.

Embodiment

In order to enable those skilled in the art to better understand the technical solutions of the present invention, below in conjunction with the accompanying drawings to this reality Be described in detail with new, the description of this part be only it is exemplary and explanatory, should not be to the scope of protection of the utility model There is any restriction effect.

As shown in figs 1 to 6, the concrete structure of the utility model is：One kind quickly detects dress for Aircraft Vectoring System Put, including mutually fasten and the hollow body 1 of formation, radio frequency component, control assembly, power supply are provided with 1 cavity of body Component, surface is provided with display, and is electrically connected between the radio frequency component, control assembly, power supply module, display；It is described The side of body 1 is provided with guidewire lumen 2.

Preferably, the guidewire lumen 2 is rectangular hollow cavity, is connected by dovetail slide 201 with body 1；Under directed cavity 2 Portion is provided with guide rail 24, and guide rail stage casing is provided with fixed seat 23, and 23 both sides of fixed seat are provided with sliding seat 22；The sliding seat 22 On be provided with wire box 21；21 bottom of wire box is provided with sliding slot 210, is provided with sliding slot 210 and sliding block 211；211 upper surface of sliding block Wrapping post 212 is provided with, lower section is provided with sleeve 213；The sliding seat 22 is provided with the boss 221 coordinated with sleeve 213.

Preferably, it is provided with flexible restoring organ between the fixed seat 23 and sliding seat 22.

Preferably, the flexible restoring organ includes the spring 25 being arranged between fixed seat 23 and sliding seat 22, slides For seat 22 towards bayonet lock 222 is provided with 23 end face of fixed seat, 23 corresponding end-faces of fixed seat are provided with pin hole 232；232 bottom of pin hole Portion is provided with elastic clamping block 233, and 233 lower part of elastic clamping block is provided with elastic component 234, and top is provided with the lockhole with exterior perforation 231。

Preferably, 21 bottom of wire box is provided with lock pin 213 matched with lockhole 231.

The radio frequency component includes wireless radio frequency modules, its antennal interface of antenna and connection circuit；The control assembly Including control board, control panel and connection circuit；Power supply module includes storage battery, charging interface, connection circuit.

When specifically used, by the control panel on 1 surface of body, various analogue navigation signals may be selected and pass through radio frequency component Antenna wireless transmitting, indicated when aircraft receives corresponding analog signal after the processing of airborne corresponding computer accordingly Shown in device, MFD or pingxian, this equipment limits from weather reason and working environment.

The test philosophy of 1.1 localizer receivers

A. one group of analog signal is launched by the antenna in radio frequency component to verify the ability to work of localizer receiver.Mainly Simulation is deviated to the left, is deviated to the right and the signal of center, and localizer receiver receives this audio being added through two kinds of components After the carrier signal of signal modulation, the angle at drift off the runway center then is measured by contrasting the component of two kinds of audio signals, And shown on machine in pathfinder, MFD or pingxian；

B. launched by antenna and lack the signal for modulating component to test its alarm function, when localizer receiver is from signal Detection will make alarm instruction when lacking at least one set of audio signal；

C. its identification function is tested by the modulated signal of antenna transmitting band identification sound, is receiving the sound of station identification A navigation identification signal can be exported after frequency signal to stereo set on machine.

Resource needed for the test of 1.2 localizer receivers

A.90Hz, two groups of audio signals of 150Hz, the component for enough changing two kinds of signals simulate different runout informations, energy Enough conditions for individually deleting one of which or two kinds of signal imitation alarms；

B.108.10 the carrier signal of~111.95MHz；

C.1020Hz controllable audio signal is used for simulation identification signal.

The test philosophy of 2.1 downslide receivers

A. one group of analog signal is launched by antenna to verify the ability to work of downslide receiver.Main analog is inclined upwards From, degree of being deflected downwardly, and shown on machine in pathfinder, MFD or pingxian；And the signal of center, course connect After receipts machine receives the carrier signal of this modulates audio signals being added through two kinds of components, then by contrasting two kinds of audio signals Component measure the angle with glide path center；

B. launched by antenna and lack the signal for modulating component to test its alarm function, slide receiver instantly from signal Detection will make alarm instruction when lacking at least one set of audio signal.

Resource needed for 2.2 downslide receiver tests

A.90Hz, two groups of audio signals of 150Hz, the component for enough changing two kinds of signals simulate different downslide information, energy Enough conditions for individually deleting one of which or two kinds of signal imitation alarms；

B.329.15 the carrier signal of~335.00MHz.

The test of 3.1 voll receivers is former

A. one group of analog signal is launched by antenna to verify the ability to work of voll receiver.Main analog can be covert, Benchmark phase, the signal of subcarrier.After voll receiver receives this carrier signal modulated by bearing signal, pass through benchmark Azimuthal error is measured in comparison covert Xiang Yuke, and is shown on machine in pathfinder, MFD or pingxian；

B. launched by antenna and lack the signal for modulating component to test its alarm function, when voll receiver is from signal Detection will make alarm instruction when lacking at least one set of signal；

C. its identification function is tested by the modulated signal of antenna transmitting band identification sound, is receiving the sound of station identification A navigation identification signal can be exported after frequency signal to stereo set on machine.

Resource needed for 3.2 voll receiver tests

A.108.00 the carrier signal of~117.95MHz；

B.30Hz can in a disguised form, benchmark phase, 9960Hz be used as subcarrier audio signal；

C.1020Hz controllable audio signal is used for simulation identification signal.

The test philosophy of 4.1 beacon receivers

A. one group of analog signal is launched by antenna to verify the ability to work of beacon receiver.Main analog far from the table, in The signal of platform, close-table, beacon receiver are received after the carrier signal of modulates audio signals, can send signals to a little expose Answer it is remote, in, close-table indicator light, and have corresponding audio prompt.

Resource needed for the test of 4.2 beacon receivers

A.75.0MHz carrier frequency；

B.400Hz the controllable audio signal of platform, 3000Hz close-tables in far from the table, 1300Hz.

The use of guidewire lumen, as shown in figure 3, charging wire 20 bypasses wrapping post 212 into S types, head and afterbody are pierced by respectively 21 both ends of wire box, in use, wire box 21 is taken out, pull 20 both ends of charging wire to extend charging wire respectively, during pulling, figure Shown in 3, charging wire 20 pulls wrapping post 212, sliding block 211 is slided in sliding slot 210；During storage, shown in Fig. 2, by fixed seat 23 The bayonet lock 222 of the sliding seat 22 of both sides is locked into pin hole 232；Then the sleeve 213 of 21 bottom of wire box is placed on the convex of sliding seat 22 On platform 221, at this time, 21 bottom lock pin 213 of wire box is just above lockhole 231, and after pushing, lock pin 213 is by under elastic clamping block 233 Pressure, the sliding seat 22 being locked depart from fixed seat 23 and are resetted under the action of spring 25 to both ends rapidly, the set on sliding seat 22 The band movable slider 211 of cylinder 213 moves, and charging wire 20 is withdrawn；Common, can all there be connector at 20 two of charging wire, can be stuck in wire box Outside 21, prevent charging wire 20 from fully entering in wire box 21.

It should be noted that herein, term " comprising ", "comprising" or its any other variant are intended to non-row His property includes, so that process, method, article or equipment including a series of elements not only include those key elements, and And other elements that are not explicitly listed are further included, or further include as this process, method, article or equipment institute inherently Key element.

Specific case used herein is set forth the principle and embodiment of the utility model, above example Illustrate to be only intended to help the method and its core concept for understanding the utility model.The above is only the preferred of the utility model Embodiment, it is noted that due to the finiteness of literal expression, and objectively there are unlimited concrete structure, for this technology For the those of ordinary skill in field, on the premise of the utility model principle is not departed from, some improvement, retouching can also be made Or change, above-mentioned technical characteristic can also be combined by rights；These improve retouching, change or combination, or not It is improved that the design of utility model and technical solution are directly applied into other occasions, it is regarded as the protection of the utility model Scope.

Claims (5)

1. one kind is used for Aircraft Vectoring System device for fast detecting, it is characterised in that including hollow for mutually fastening and being formed Body（1）, the body（1）Radio frequency component, control assembly, power supply module are provided with cavity, surface is provided with display, and institute State and be electrically connected between radio frequency component, control assembly, power supply module, display；The body（1）Side be provided with guidewire lumen （2）.

2. one kind according to claim 1 is used for Aircraft Vectoring System device for fast detecting, it is characterised in that the conducting wire Chamber（2）For hollow cavity, guidewire lumen（2）Lower part is provided with guide rail（24）, guide rail stage casing is provided with fixed seat（23）, fixed seat （23）Both sides are provided with sliding seat（22）；The sliding seat（22）On be provided with wire box（21）；Wire box（21）Bottom is provided with cunning Groove（210）, sliding slot（210）Inside it is provided with and sliding block（211）；Sliding block（211）Upper surface is provided with wrapping post（212）, lower section is set It is equipped with sleeve（213）；The sliding seat（22）It is provided with and sleeve（213）The boss of cooperation（221）.

3. one kind according to claim 2 is used for Aircraft Vectoring System device for fast detecting, it is characterised in that the fixation Seat（23）With sliding seat（22）Between be provided with flexible restoring organ.

4. one kind according to claim 3 is used for Aircraft Vectoring System device for fast detecting, it is characterised in that the elasticity Resetting-mechanism includes being arranged at fixed seat（23）With sliding seat（22）Between spring（25）, sliding seat（22）Towards fixed seat （23）Bayonet lock is provided with end face（222）, fixed seat（23）Corresponding end-faces are provided with pin hole（232）；Pin hole（232）Bottom is set It is equipped with elastic clamping block（233）, elastic clamping block（233）Lower part is provided with elastic component（234）, top is provided with the lock with exterior perforation Hole（231）.

5. one kind according to claim 4 is used for Aircraft Vectoring System device for fast detecting, it is characterised in that wire box（21） Bottom is provided with and lockhole（231）Matched lock pin（214）.