DE2238615C2 - On-board autonomous bad weather landing procedure - Google Patents

Description

the automatic tracking system e.ngeeeben will

2. Landing method according to claim I, characterized characterized in that the target area is found by passive microwave imaging.

3. Landing method according to claim 1, characterized in that the target area is image-wise active can be displayed via a time gate-controlled laser illumination.

4. Landing method according to claim 1, characterized in that the target area image-wise can be displayed passively via an infrared viewing device.

5. Landing method according to claim 1, characterized in that the target area by means of a Radar vision device for the rough adjustment of the target area can be displayed.

6. Landing method according to claims 1 to 5, characterized in that a microwave altimeter Is used.

7. Landing method according to claims 1 to 5, characterized in that an acoustic Altimeter is used.

8. landing method according to claims 1 to 4, characterized in that the selected Landing point by a servo-guided, stabilized laser altimeter and range finder is continuously measured.

The invention relates to an on-board, low-weather landing method in which the Finding the landing point an on-board viewing device used and the landing point is continuously measured from on board, the measurement results together with the values for altitude and distance are always available to the pilot.

Various types of autonomous landing procedures have already become known. One of these The method provides that the visual information from or on board via radar and screen display, bad weather landing procedure

* ^{5 to realize} ' ^{which avoids} the disadvantages mentioned and which is especially suitable for difficult missions, such as in extremely poor visibility.

This object is achieved in that .

^a ) the landing target point is found, determined ^and visually displayed together with the flight status data ^{by means of a} laser bad weather ^{indicator on board,}

^b ) ^{the guide beam for the} aircraft itself is generated and tracked by ^{means of an} inertial system-stabilized laser altimeter and range finder, and

^c ) ^{All ground obstacles and the} precision height in the final landing phase ^{must be} determined ^{using a} laser low height and range finder and ^{entered into the automatic} tracking system in terms of value.

The new process brings the additional advantages that autonomous landings can also be carried out in fog and blowing snow, furthermore that the pilot receives information about the distance and altitude with respect to the selected touchdown point are continuously available and that any landing trajectories are possible, depending on from the distance to the selected Aufselzpunkt the latter can be changed by the pilot. However, the proposed measures also allow the aircraft or missile to be used in all cases in which no radio aids are possible, but also in all cases in which radio emissions to the outside world are not permitted. Radar- and Doppler methods cannot be used here. This is especially true for operational flights behind enemy lines, vertical or steep take-off or landing operations on unprepared runways, etc.

It is also proposed that the target area be found by passive microwave imaging or that the target area can be actively represented in terms of images via a time-gate controlled laser illumination is. These measures result in high-contrast representations even in the worst viewing conditions of the target or landing area.

Furthermore, one embodiment of the invention provides an infrared viewing device. the

requirement that the target area passively via television monitors in the cockpit,

an infrared viewing device can be displayed. This makes possible, for example, irag

Measures are any emissions of ^Corridor gf ^ren J ^{n. de} _p ^m _H ^ ^O Fiu «ustand" cin "g7blendetrso

avoided on the outside. 5 information about the flight connection,

^{For quicker coarse adjustment of the vision} device that the pilot does not go ^far ""! NSt ^ ^C "X _cnd J ^ s Än-

it may be advisable that the target area must be observed when approaching Oa s «io _fcorrek

fine radar display device shown to the pilot flight «- ^" ^^^ t is the zLab.age at

In those cases in which the recognizability of Bo- io arrival in the target area is extremely low, we are with you

the obstacles play an insignificant role :, help of the laser control device; 10 der Meßstrah ^ des

can instead of a laser-milled low-height measuring platform-stabilized L ³ I """ _ausi " aligns and

sers also a microwave altimeter use meter "on the ^ P £ _{ichtung and}

find dung; This landing point of the tmiernu is also an acoustic altimeter. g, &

usable in the context of the invention. «5 the height still _c ^during ., ^D " _n i _nd et _e s Zielk ™

An exemplary embodiment of the invention also provides. A viewing device ^^^^ Z-

It is necessary that the selected landing point is passed through one which the exit "te" rvojs ^ ^

servo-guided laser stabilized in elevation and decision tezechne voltage diameter, _ir w o coverage brought

rangefinder is measured continuously. By this chosen AufseUpunk to u ^ J ^. ^

manufactures the radar systems known to ^{S bishir}

-Se-BSi; is nachfo, _g end at an execution ^^^^

example and various possible applications on the landing point ^ _land

opportunities described and drawn «. It shows ^by ί ^ ΛΪ ^ Ϊ !? ^ kU5. the

1 shows a pictorial representation of an approach, the aircraft produces P ™ " ¹ " ™

chances described and drawn «. It shows ^d ίΛΪ ^ Ϊ !? ^ kU5. the Gs. ^ _;

1 shows a pictorial representation of an approach when the aircraft produces P ™ " ¹ " ™ would _{like to go} .

F i g. 2 a pictorial representation of the monitor image itself. In order to now over possible Hn

des in the final approach phase, conditions, over treetops over and e.tungenu ^ ..

Fi * 3 a b ^ cne D ^ position of the Momtorbi, - 30 ^^ S ^ SSSTS ^^ S Ϊ feet

^ ¹ To Αηΐ since ^e t s gewäh.te target area is as Ä scratch% ™ ^% *% _

Navigation aid that is in front of any aircraft on ^ *> ^^^ ™^! £ ^ c _n

handene system, for example Träghe.ts-navigation-making itself can aut ^ ^runa _{Availability checked "cash Tr} ä _R -

tion systemf used ^ which depending on the flight duration 35 ^ ^rdl "^ _s ⁿ ^ _h 7 _a ⁿ _u ^g _tO rnatically a alch'anucli

for the target area more or less large inconsistency system both ^autom "'j ™. _h j _nun . _dc ,

inaccuracies. For fine navigation in the destination. Zur ^KhnelIerc "" ^ ¹ ^^ that en

To find the landing site and to guide you to the target area, e ™ ^ "^ ^ _T ' _to % _zo ^ _n

pulling the Aufset, _P oint, Hérange independent of a.len Bodenhil- R ^ ^to ^ -Sftgem obcinpe.lung

fen, bad weather and visibility, is 40 and that in the halls m .JJ

Board the inventive bad weather capable ^ J ^ ⁿ ^ ^m ^ ü d

Bord the inventive sch.eg f ^ J ^^^ _T Zi ^ & ir _i n _i

autonomous landing support system. Recognizability of who »ger ^u f _d ; . _{height screed}

This system is made up of a laser sighting device at the end of the ^L ^ 5 " ^PrdZ '« ° " _v [™

10, a servo-guided platform-stabilized la- a microwave-high ^

se; height and range finder 11 and a 45 The landeve according to the invention, ™ J ™ «^" ^s J _f J

Laser low altimeter and range finder 12 especially for M.ssions, I ^{bei dencn} £ ^ f _n ^ Vh _e "

together. The laser sighting device 10 supplies the Kor- is excluded or from ° ' ^ute »^ f _o f ^ ^C ^"

Information required to correct the inertial navigation. Of course ^dl ^ Kombmat on with at

mations and enables the pilot to find their Nav.gat.onssystemen, * ^ie ^ PJ'J ^ ¹ ^^ of the landing site in the target area. Here the 50 Aerea-Navigati ° n, to m the ^^^^^.

Image acquisition possible either actively via a time gate control point. Nebel or ^an « ^re jeMechtejj.cn

ertes laser lighting process carried out, ratios (down to almost zero) are now playing

or it takes place passively via a microwave or flight and landing core role.

1 sheet of drawings

Claims (1)

"'ΐ Claims: 1. On-board autonomous bad weather Lan de-procedure in which an Ijord-side viewing device is used to find the landing point this landing point is continuously measured from on board and these results together with the widths for altitude and distance are always available to the pilot, characterized in that a) by means of a laser bad evaluation device go on board the landing point, is determined and visibly displayed together with the flight status data, b) by means of an inertial system rod. T ;, mV ™ ,? ^{E "tfernun} g ^s ™ * ^ter is pursued and ^the and is won. This known method has the disadvantage that the image information is practically only at known terrain (e.g. airfields) can be interpreted and that the distance and height information in it of the selected touch-up point is not included. Another known method of this type also uses radar imaging. It has the Disadvantage that radar reflectors have to be set up on both sides of the preselected runway. Therefore, one cannot speak of an autonomous landing procedure here. All radar arrangements have the disadvantage, among other things, that the contrast in the monitor image is relative bad is. It is also known to make a landing process on-board autonomous that a vision acquisition takes place by amplifying the existing residual light. This method has the disadvantage «O that in difficult bad weather conditions, such as in snow, rain or fog,