DE1170662B - Device for the remote display of the flight position of a missile - Google Patents

Description

FEDERAL REPUBLIC OF GERMANY

GERMAN

PATENT OFFICE

EDITORIAL

Boarding school Kl .: G Ol c

German class: 42 c-25/50

Number: 1 170 662

File number: S 47114IX b / 42 c

Filing date: January 18, 1956

Opening day: May 21, 1964

The invention relates to a device for the remote display of the flight position of a missile in relation to on its roll and tilt axis with a display device, on which two of a gyro horizon supplied DC voltage signals proportional to the roll and pitch angle of the missile be transmitted remotely, e.g. B. also from the missile to a ground station by wire or radio transmission.

It is known to use a cathode ray tube as an indicator for the attitude of a missile choose whose horizontal baffle with an alternating voltage of constant amplitude and their vertical deflection plates with an alternating voltage synchronous with the former alternating voltage from the roll angle proportional amplitude and phase position as well as a superimposed DC voltage are acted upon by the angle of inclination of proportional amplitude and polarity. A such a display device requires three transmission channels, namely: one channel for the rolling signal, one channel for the incline signal and one channel for synchronizing the alternating voltages for the constant horizontal deflection and the vertical deflection proportional to the roll angle. If such a If the display device is on board the missile, this multitude of transmission channels is irrelevant. However, if the device is outside of the missile, e.g. B. in the ground station, is arranged, a reduction in the number of transmission channels is urgently required in order to reduce the need for equipment To keep effort small.

The aim of the invention is to reduce the number of transmission channels required to two, whereby not only the inclination signal, but also the roll signal again in a known manner as DC signal is transmitted. Use is also made here of the option known per se made the direct voltage signal proportional to the angle of inclination to a separate, additional to switch vertical deflection means of the cathode ray tube.

The above-mentioned device for remote display of the flight position of a missile is characterized according to the invention in that in the case of a known design of the display device as a cathode ray tube, its horizontal deflection plates with an alternating voltage of constant amplitude and its vertical deflection plates with one of the first-mentioned alternating voltage synchronous alternating voltage of the roll angle proportional Amplitude and phase position are applied, and when setting up for remote display of the flight position
of a missile

Applicant:

Sud-Aviation,

Societe Nationale de Constructions

Aeronautiques, Paris

Representative:

Dipl.-Ing. R. Müller-Borner

and Dipl.-Ing. H.-H. Wey, patent attorneys,

Berlin 33, Podbielskiallee 68

Named as inventor:
Lucien Servanty, Paris

Claimed priority:

France of January 21, 1955 (684 038)

known circuit of the direct voltage signal proportional to the angle of inclination to a separate, additional deflection means the amplitude and phase position of the on the vertical deflection plates switched AC voltage according to the amplitude and the sign of the roll angle proportional DC voltage signal is set.

In this way, the AC voltages are synchronized without an additional channel for the constant horizontal deflection and the vertical deflection proportional to the roll angle.

An embodiment of the invention is described below with reference to the drawing. It shows

F i g. 1 is a schematic perspective view of a horizon gyro located in the missile; the two DC voltages that vary proportionally with the angle of inclination and roll of the missile generated,

2a shows a simplified circuit diagram of the inventive Transmission and display device,

FIGS. 2b, 2c and 2d show examples of flight attitude displays, as they are obtained with the display device according to the invention.

According to FIG. 1, the horizontal gyro contains a rotor 1, the rotor shaft 2 of which is kept constantly vertical by known means. The rotor shaft 2 is

409 590/125

mounted in a rotor arm 3 which is provided with bearing journals 4 extending perpendicular to the shaft 2 and is freely rotatably suspended in a cardan bracket 5, which in turn by means of a perpendicular to the bearings 4 and axis 6 lying in extension of the center of gravity of the rotor 1 on a support 7 is hung. The support 7 is so firmly attached on board the missile that the geometric Axis of the bearings 4 parallel to the inclination or

circle, post-acceleration circle, etc., as well as the usual setting means provided in such a tube been omitted.

The horizontal baffles 22 are made from one parallel to the ends of the potentiometer 27 switched AC power source 26 fed. The vertical baffles 23 are with a center tap 28 or with the sliding contact arm 29 of the potentiometer 27. Thus the hori-

the roll axis of the missile is while the io zontal and vertical baffles have the same axis 6 fed in parallel to the other of these two axes phase currents.

The horizontal baffles receive a voltage U _n = A cos ο t, where A is a constant, while the vertical baffles with a chip

is. In the example shown it is assumed that the
Axis 6 is parallel to the roll axis. The axis 6 is
hollow and behind the support 7 via a (not shown) rotatable connection with a compressed air source 15 voltage U _v = b cos <ot are fed, with b a

tied together. The axis 6 is positive or negative with an extension 8, depending on the position of the

see, which is formed into a nozzle, the tang sliding contact arm 29 has changing value. Thus,

tial to the rotor 1 can blow air and the luminous point writes a straight path that

Rotation of the same is maintained, for example by being horizontal when b = 0, d, h. the sliding contact effect on small blades or on its periphery 20 arm 29 is in the middle position, or the

provided wells. more or less in one direction or the other

On the cardan bracket 5, a potentiometer 9 device is attached according to the deviation of the Kontaktstarr, the sliding contact arm 10 is inclined with poor from the central position. The sliding one the bearing pin 4 is connected, the axis of which is contact arm 29 on the shaft of the moving coil one by the stabilizing effect of the rotor 1 always 25 measuring device, such as a voltmeter, attached that is held horizontally. Under these conditions a voltage is obtained that is proportional to the voltage causes any angular displacement of the flight 15,16, which in turn is proportional to the roll angle body around the inclination axis is a relative angular of the missile. Thus, the display organ is for moderate adjustment of the same amplitude of the potential real horizon, that by the light tiometer The straight light track 31 described with respect to the fixed sliding contact point is formed taktarm 10. Three lines 11 are provided, which is always inclined at an angle on the screen, the potentiometer with the on the axis 6 in front of the roll angle of the missile opposite the seen and belonging to the grinding brushes 13 corresponds to the true horizon. Connect switching segments 12. The additional vertical deflection coil 24 is with

Similarly, another potentiometer 35 is fed with a current that is proportional to the voltage 14 fixedly attached to the support 7, the sliding 10 to 17 of which is in turn attached proportional to the contact arm 15 on the axis 6, which is fixed at the angle of inclination of the Missile is. Therefore verdem cardan bracket 5 is connected. Under these conditions, this coil causes a vertical deflection of the conditions causing any angular displacement of the true horizon representing light trail 31 after the missile about its roll axis a relative 40 up or down, which corresponds to the angle of inclination of the angular displacement of the same amplitude of the missile in relation to the true horizon entPotentiometer 14 in relation to its stationary speaks.
Slide arm 15. Figs. 2b, 2c and 2d show various types

Thus it is possible, if a suitable elec- Views of the index line or the horizontal bar

tric power source, such as one shown in the drawing on the instrument. For the sake of clarity, the

did not show battery, connected to potentiometer 14 drawing the usual reference miniature airplane

is shown between the sliding contact arm 15 and the central. F i g. 2 b corresponds to the straight ahead and

tapping 16 to take a stream that corresponds to level flight. Fig. 2c shows the right bank

Roll angle of the missile is proportional, with the missile and Fig. 2d a descending

the polarity of this current from the inclination sense 50 right curve. If desired, the tracer can

(to the right or to the left) is dependent. in the familiar way instead of the true horizon

Similarly, it is by inserting a represent the rear view of the missile, wherein

Direct current in the potentiometer 9 possible, between the then displayed relative movement that of the flight

between the sliding contact arm 10 and the central body with respect to the true horizon and

tapping 17 to take a current, the propor- 55 not, as just described, the apparent movement

tional is the angle of inclination and its polarity of the horizon with respect to the missile. to

of the direction of inclination (upwards or after this purpose, it is sufficient, for example, to specify the direction in the

below) is dependent. Polarity of the batteries shown in the drawing.

The scheme according to FIG. 2 a shows the receiving input The connection between the scanning and receiving

direction of the inventive artificial honing 60 catching parts of the device is transmitted through

zontes. This receiving device contains lines V ₁ and F _{2 of} some kind, for example through

Cathode ray tube 18, which is the actual indicator telephone cable or radio channels, causes the loading

is. 21 is the electron beam source of this tube, is known and is therefore not described here.

22 are their horizontal baffles, 23 are their direct current powered potentiometers 9

vertical baffles, 24 an additional baffle 65 and 15 can be powered by alternating current

coil and 25 the screen. For reasons of association- changeable capacitors or self-inductions

the various supply circuits of the Ka- are replaced, whereby the one achieved in this way is then modulated

cathode ray tube, such as cathode heating circuit, anode current converted into direct current in a known manner

before it is placed in the receiver of the device.

Similarly, the potentiometer 27, 28, 29 can be replaced by one that is tapped in the middle inductive turntable, for example by means of a transformer tapped in the middle, which has a rotatable Primary winding and which produces an output proportional to the angular position of this Winding is. This winding is then controlled by the device 30. The phase of the output voltage 28, 29 is equal to the phase of the input voltage 26 or shifted by 180 °, whereby the necessary Phase equality of the vertical and horizontal deflections is guaranteed. Furthermore, instead of the Potentiometers 27, 28, 29 a pair of variable capacitors between the input 26 and the vertical deflection circuit are switched on, the plates of the capacitors through the device 30 being controlled.

To adjust the device are in the transmission channels in a known manner by hand to be operated adjustment means provided.

Claims (2)

Patent claims: 1. Device for the remote display of the attitude of a missile in relation to its roll and Inclination axis, with a display device on which two delivered by a gyro horizon, remotely transmit DC voltage signals proportional to the roll and pitch angle of the missile are, characterized in that in a known design of the display device as a cathode ray tube (18), the horizontal deflection plates (22) of which with an alternating voltage of constant amplitude and their vertical baffles (23) with one of the former AC voltage synchronous AC voltage are acted upon by the roll angle of proportional amplitude and phase position, and with the known switching of the direct voltage signal proportional to the angle of inclination to a separate, additional vertical one Deflection means (24) the amplitude and phase position of the switched to the vertical deflection plates (23) AC voltage according to the amplitude and the sign of the roll angle proportional DC voltage signal is set. 2. Device according to claim 1, characterized in that for setting the on the vertical deflection plates (23) to switch AC voltage with a potentiometer (27) Center tap (28) is used, whose resistance track with which the horizontal deflection plates (22) applied alternating voltage of constant amplitude is connected and its wiper (29) from the rest position opposite the center tap (28) by means of a voltmeter similar device to which the direct voltage signal proportional to the roll angle is applied (30) is adjusted, the desired AC voltage between the grinder (29) and the center tap (28) is removed. Considered publications:
German Patent No. 693 036;
Swiss Patent No. 224 235;
British Patent No. 496,521;
U.S. Patent Nos. 2,463,529, 2,637,911. 1 sheet of drawings 409 590/125 5.64 © Bundesdruckerei Berlin