JPS58190712A - Artificial gyroscopic horizon - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

[Detailed Description of the Invention] This invention is a type of light that is used to project a line or strip of light in front of the pilot and control the position and attitude of this edge to lower the plane to a true level landing gear. Regarding the artificial horizon.

In this specification, the term ``aircraft'' shall include flight simulators and aircraft in general that move in three dimensions.

Aircraft typically have a device that indicates the orientation of the aircraft relative to the horizon. This device is installed in the cockpit so that the pilot can periodically monitor the cough device to know the attitude of the aircraft if the pilot cannot see the horizon. Therefore, pilots must use central vision that spans approximately 3 degrees in front of their eyes.

Central vision uses devices such as artificial horizons, and pre-kappa coding (which provides a sense of spatial position and orientation).
(decoding) and provide a sign that leaves interpretation unresolved. On the other hand, limbic vision recognizes linear objects within the limbic field of vision and transmits information regarding their motion to the brain area that responds to motion perception (κ).
d@dicat@d - hrd-wi red -c
i rcuit) is used unconsciously to recognize movement in everyday situations. Therefore, all the devices that provide information about the motion of the pilot's aircraft by the pilot's peripheral vision are
It uses the oJ route and frees the pilot's instinctive thinking from the constant task of interpreting signs.

Since it is impractical to increase the dimensions of existing artificial horizons so that they can be visually perceived by peripheral vision,
No means should be devised 7'1 to project information onto the standard instrument panel that can be perceived involuntarily in the incisal field of vision. Most known visual targets: 4! An effective method is to project a beam of light onto a standard equipment spring from a projection device equipped with means for moving the beam of light relative to the aircraft for horizontal display. .

A method for producing a beam or streak of light in front of the eye that is monitored by limbic vision is disclosed in U.S. Pat. No. 4,083,23.
It is disclosed in No. 9 Akira #1 Tatami. A light source is disposed within the nozzle, one portion of which is tilted and the other portion rotated to move an element that projects a beam in front of the pilot. The motion of the section is related to the gyroscopic platform of the aircraft so that this honor always displays the true horizon. Although this structure can be used for one purpose, it is extremely expensive, making it difficult to install it in the cockpit of an existing aircraft. However, this construction has the disadvantage that the extreme temperature changes and movements of the mechanical elements subject to acceleration forces make the use of the device in aircraft such as fighter jets dangerous.

An object of the present invention is to provide an artificial horizon constructed so that only the projection head can be placed in the cockpit and the light source can be placed at a position away from the cockpit when the overall dimensions are small and space constraints are large. The goal is to provide the following.

There are two conflicting design criteria for spacing light sources. In order to project light streaks that are visible even under sunlight,
The light source must be powerful. However, such a light source is undesirable from a power consumption and safety point of view (needing to reduce the efficiency of the transmission).On the other hand, in the absence of sunlight, the illuminance of the light strip is Since the illuminance would be too strong, it is also desirable to provide a means for changing the illuminance of the striations.

In this case, if there is enough space in the cockpit, the light source and projection head can be placed inside the cockpit. Due to design criteria, it may not be necessary to separate these two parts. 1st
In addition, the projection head must be rigidly mounted on the aircraft to avoid positional errors of the beam due to vibrations and accelerations.

Second, the light source should be installed next fall to limit the possibility of vibration-induced depletion. In order to meet these completely contradictory criteria, it is necessary to place the two parts in close proximity to each other.

Accordingly, the present invention provides an artificial horizon having a limited intensity light source that can be mounted remotely from the cockpit of an aircraft.

A scanning mechanism that receives light from this light source and projects a light beam is installed within the cockbit. Mosquito scanning mechanisms project a ray representing the true horizon by scanning a light beam at a high enough wavenumber that a continuous image is perceived.

The invention will be better understood by reference to the following description in conjunction with the accompanying drawings.

FIG. 1 shows an equipment panel 20 used by the pilot and co-pilot. The pilot and co-pilot sit behind the controls 22 and 24, respectively. The equipment on the left side of the center of the panel is almost the same as the equipment on the right side, so that both the /ζ pilot and co-pilot can operate the reactor aircraft. #The equipment panel includes a pair of artificial horizons (26.28), which are commonly installed in aircraft tunnels (of this type of equipment) and are used to monitor pitching and rolling of aircraft relative to horizon. is displayed to the pilot. These horizons are relatively small and the pilot must use his central vision to look at them, forcing the pilot to take his eyes off the windshield and other equipment when looking at the horizon.

1 shows the positions of two striations produced by the apparatus of the present invention, and will now be described with reference to FIG. 2 and subsequent figures. These two positions are indicated by reference numerals 32 and 34. At position 32, the center of the ray lies on the horizon 26, which in this example serves as a reference point. Therefore, the aircraft is flying horizontally with its left wing down. In contrast, the rays 34 indicate that the aircraft is flying L7 with the nose down at an angle of 41N with the JI in a water-F bow. This is primarily evident from the fact that the equipment within the equipment panel 20 is housed within a rectangular frame having horizontal and vertical sides. This arrangement therefore indicates whether the rays are horizontal to the instrument panel 20 and therefore whether the aircraft is rolling. Similarly.

The fact that the rays 32 are inclined with respect to the device means that
Indicates that the aircraft is rolling in that direction.

In this aircraft, the equipment does not have rectangular surfaces, but is arranged in horizontal rows. If the equipment is not arranged as described above in the aircraft on which the device of the present invention is to be installed, a reference must be provided on the equipment panel. This reference would have to be provided in the form of a line or series of lines extending horizontally on the instrument panel, including a specific line indicating that the aircraft is in level flight.

It is clear that if the co-pilot is also to use a ray, he must project two rays. The reason is,
If a single ray extends across the instrument panel, the pilot and co-pilot will receive different information from the ray as the ray slopes upward at one end and downward at the other as the aircraft rolls. This is because it would result in a violation of the law. Two beams can be created by using a Z edge of the type described next (by using two beams, or by splitting the light into two images or by concentrating the beam in front of either the pilot and co-pilot). It can be formed by including one marginal horizontal scope of the type described below, together with suitable optical equipment to do so.

Refer now to FIG. FIG. 2 schematically shows the main parts of an artificial horizon which is a preferred embodiment of the present invention.

The projection head 36 receives light from a laser light source 38 via a removable connecting member 40 . The connection member 40-1 includes an optical fiber, which will be described later, as one optical transmission element. The laser light source 38 is inserted into the housing 42 and is driven by one circuit on the perforated side. The control circuit receives signals carrying information related to the rolling of the aircraft from the aircraft's gyro platform via three input lines 44 and receives information regarding the pitching of the aircraft via three relay connectors 46. Receive.

A power input line 48 is also provided. As discussed below, the control circuit uses information coming from the Mukuro Gyro platform to drive the scanning mechanism to control the position of the rays so that the pilot sees a continuous shadow 50 representing the true horizon. .

FIG. 3 is a sectional view showing the inside of the projection head 36. As shown in FIG. As shown in the figure, light entering from the connecting member 40 (FIG. 2) in the direction of arrow 52 is incident on the first inclined @54. This casting normally lies in a plane making an angle of approximately 45 DEG to the direction of the light beam 52, and the light reflected by this key is incident on the second -56.

Also the second furnace. It makes an approximately 45° angle to the direction of light passing between these two keys.

These mirrors are arranged to cooperate to project light from the projection head through the aperture 58 to project the beam 50 (FIG. 2).

The first 954 forms part of the first scanning mechanism 60 . The scanning mechanism 60 includes a rod 62 to which the mirror is attached.
The mirror rotates around the rod axis together with the rod. Similarly, the second mirror 56 is attached to a rod 64 that forms part of a second scanning mechanism 66. As will be described below, the scanning mechanisms 6LJ and 66 are independently driven so as to optically cooperate to scan the incident light 52 to produce a pilot-bearing ray. The position of the rays is controlled by the scanning motion of the towara, as described below.

In Figure 4, the six positions of the rays are indicated by reference signs "a" to '"f#. In Figure (a):
The honor is invited to a position that stretches out on both sides of the Motosou point. In order to display honor in front of the pilot,
The light projected from the projection head 36 (21.'') must emit -Ai at a frequency sufficient for the pilot to perceive the beam as a continuous beam. preferable? The frequency used in the M example is 40 cycles per second. Thus, as shown in FIG. 4(a), the light is shown relative to the zero point 67 and scans between the six values "h". When the aircraft begins to raise the mechanism for climb, the rays descend from the reference point and take a negative value of 1■ as shown in Figure (b)K.
”.

Therefore, from Figure 1 (a) and (b), when the aircraft is not rolling, scanning using the first key 54 results in 2
It is clear that the striations can be produced by positioning the second mirror 56 to exhibit a vertical displacement with respect to pitching. However, if the aircraft lands first and rolls with its right wing pointing down without pitching, the light should take the position shown in Figure (C).

This striation can only be produced by synchronized movement of the mirrors 54 and 56 (FIG. 3) such that the first mirror 54 exhibits a horizontal movement and the second mirror 56 moves in conjunction with the vertical movement. I can do it. In fact, one point on the rays causes the first mirror to be moved by an angle corresponding to the cosine of angle A and at the same time the second mirror to be moved by an angle corresponding to the sine of this angle. When the resulting 6 mirrors are moved synchronously, the angle of the rays with respect to the horizontal position (angle A) is a function of the strength of the signal supplied to the scanning mechanism 60.66 to control the movement of these mirrors 56. By simply changing
The first three figures in Figure 4 show the effect of the first bell when scanning the rays. Let's do it.

Figure (d) Fi shows the situation that occurs when the aircraft rolls 90'. At this point, the first mirror is stationary and the second mirror causes the scanning movement of the light beam. In reality, this position is a natural deviation from the position shown in Figures (&) and (C).

Takeover: The aircraft rolls through the position shown in figure (c) and enters the position shown in figure (d). Complications arise when Kasu Aircraft rolls considerably and pitches at the same time. It is clear from the above figures that both bells must be moved in response to rolling to move the light.

But still.

The two mirrors must move to also reflect pitching. This becomes clear by comparing Figures (b) and (d). In the state of Figure (b), pitching is indicated by the set position of the second mirror 56.

If the rays shown in figure (d) have to move in response to pitching, this movement is obtained by adjusting the first @154. Therefore, at any position between these extremes, pitching must be represented by the combination of the movements of the two mirrors. In figure (e), the coordinates of the ends of the striations relative to the reference point are shown. (
Comparing Figure e) and Figure (f), it can be seen that the ray can take a position where both coordinates at one end are positive and both coordinates at the other end are negative; Other positions are possible, such as t'Lk, where three coordinate values are positive and one coordinate f is negative. Obviously other positions are possible if the aircraft rolls 3600 with pitching.

To introduce pitching into the scanning mechanism, consider the rays to be moving in both coordinates relative to the reference point. For example, in figure (e), the center of the ray is along the horizontal axis.
It has moved a distance equal to the product of pitching and 5ine A. Similarly.

The vertical travel distance is equal to the product of pitching and cosine A. Considering both pitching and rolling,
For example, the upper end point of the ray in figure (e) has the following coordinates.

X=Constant XcosineA+Pitch X5ine AY
= Constant X5ine A + Pitch Xcosine A
Since cosine A is negative, the vertical value of pitching is subtracted from the first value for rolling.

Similar results can be obtained using figure (f).

the first mirror has a scanning movement in the horizontal or X direction;
It is clear that the second mirror scans in the vertical or Y direction. The above equations show that each of the scanning mechanisms 60, 66 is controlled by a signal consisting of two major parts, related to rolling and pitching, respectively. clearly.

A control unit contained within housing 42 (FIG. 2) analyzes signals from connectors 44.66 of the gyro platform and transmits these analyzed signals to scanning mechanism 60.66.
66. Before describing the central circuit, the discussion of mechanical elements will be completed by describing the mechanical connectors used to attach the flexible connecting members at their ends.

Refer now to FIG. FIG. 5 shows a flexible connecting member 4
The connector used to connect the laser light source 38 to the laser light source 38 is shown. As shown, the left end of the connector is attached to the threaded cylindrical projection 68 of the laser source 38 by a threaded ring 70. The ring 70 is connected to the outer conical portion 7 of the intermediate member 74.
It has an inner conical portion that engages the 2. , thus ring 70 precisely aligns intermediate portion 74 with the light to be emitted from the laser light source along the axis of the intermediate member. The light travels as a substantially parallel light beam to the lens mounting member 78.
and enters the converging lens system 76. This lens attachment member is positioned by a ring 80. The outer surface of the ring 80 is provided with threads to engage with threads provided in the lens collar member 78. The other end of the intermediate member 74 is provided with a conical inner surface 82 that widens outward to receive the 1M element 84 . Terminal 84 is connected to one, e.g., Amphenol Precision Fiber Optic Connector ("ANPH").
ENOL precisio? t Fiber(lpt
ic Connector"), which is attached to the flexible connecting member 40 and has an optical fiber 86. The optical fiber 86 extends to a precisely defined position at the end of the terminal 84. The light elongated and focused by the lens system enters this end of the optical fiber 86 and is transmitted to the projection head 36 (FIG. 2).The connection configuration shown in FIG. The same is true at the end of the flexible connecting member 40, with the difference that the lens system at the other end is arranged to receive and collimate the light diverging from the optical fiber 86.

In the preferred embodiment, optical fiber 86 is a single optical fiber having a diameter of 50 microns. This optical fiber was selected in consideration of the conditions at both ends of the connecting member 400 and the minimum strength of the connecting member.

At the end shown in FIG. 5, it is clear that the end of the optical fiber is precisely positioned if all the light emitted from the laser beam m has to be convergently incident on the end of the optical fiber. must be done. If the power of the laser light source has to be kept to a minimum that meets power and safety requirements, as much light as possible must be transmitted without losses. This configuration is 2 to 3 db
It has been found that at the end attached to the projection head of a flexible persimmon lumber, the diverging light from the optical fiber is able to transmit light with some degree of loss due to the optical eccentricity. problem(
off-center optics problems
) must be kept to a minimum. If the light is to be collimated, the lens system must be able to receive a single divergent light and precisely collimate this light. Although this cannot be achieved completely, collimation is improved if the divergence angle of the light emanating from optical fiber 86 is kept to a minimum. Graded-index optical fibers are preferred to minimize transmission loss.

From the foregoing, it will be understood that optical fiber 86 is a compromise. Considering the conditions at the input end shown in Figure 5, it is easy to use a large optical fiber, but at the output end the optical fiber should be as small as possible to minimize divergence. .

The control circuit will be explained in detail with reference to FIG.

The control circuit is capable of receiving signals from the aircraft's gyro platform and processing these signals to drive the scanning mechanisms 60 , 66 .

As shown in FIG. 6, input signals 44 and 46 are applied to an input signal processing circuit. This input signal processing circuit converts these signals into two digital outputs. One of the outputs represents pitching and the other represents rolling.

These signals are received by a microprocessor system which also receives signals from the control signal processing circuit. This dims the pilot.

It provides the convenience of zero adjustment and scale change. All of these signals are processed and sent to the microprocessor system where they are combined with the signals from the input signal processing circuit and are converted into digital signals and sent to the output signal processing circuit. This output signal processing circuit outputs pitching and rolling information that is sent to the scanning mechanism 60, 66 described with reference to FIG.

As shown in the signal line to the scanning mechanism.

A power amplifier is also provided.

A power supply is also provided along with an ON/OFF switch for the PJr, which is connected to both the laser power supply and the system. A helium-neon laser with a power output of 2 to 4 milliwatts is preferred.

With respect to the hole control circuit shown in FIG. 6, it is possible to vary the capacity of the microprocessor-system;
It is clear that this allows simple modifications of the device described above.

For purposes of illustration, a simplified device that can exhibit pitching and rolling is described. However, in a preferred embodiment, the intensity of the rays can be varied in response to changing conditions within the cockpit. In bright sunlight, the rays should be as bright as possible, but at night they should be slightly dimmed. The microprocessor system described above makes this improvement possible. Therefore, the difference between a device that does not have a dimming function and a device that does have it comes from the MK of the microprocessor system.

Next, a preferred method of dimming will be explained with reference to FIG. This figure shows a typical example of a waveform applied to one of the scanning jaws to cause light to be deflected along a path formed by the mirrors depending on the attitude of the aircraft. As shown in FIG. 7, the bell begins an IR phase or cycle from a position of maximum angular displacement and, over time, makes a series of stepwise movements toward the end of the cycle. When the end of this cycle is reached, the mirror returns and begins scanning again. The solid lines in FIG. 7 indicate the waveforms supplied to the scanning mechanism, and the dashed lines indicate the vertical motion. In thermal theory, the motion of the casting lags behind the waveform due to inertia. Nevertheless, since the mirror stops for a certain amount of time between each stage, it can be seen that the screen projects light that is perceived as a point during its stop period during the cycle. It will also be understood that there is extremely weak light connecting the dazzling points between the points above. This weak light is practically invisible to pilots at all. This is because the irradiation intensity depends on the scanning speed.

Areas of maximum illumination occur where scanning is momentarily stopped.

It has been found that human vision associates a straight line from seven or more points that make up 17A, thus allowing a line of nine discrete points of maximum illumination to occur. To reduce the illumination of the rays slightly, the pilot can operate a dimming control that changes the number of steps during the cycle.

Appropriate changes are from 9 points to 17 points, 33 points, 65 points,
This is a change to one continuous line.

Further dimming can be achieved by stopping the light beam at certain times during the cycle as shown in FIG. As shown in Figure 8, this cycle is 1
It consists of a series of steps followed by an angular displacement greater than that which allows the transmission of light. Above this limit, light is blocked by the trapping member into the projection head without prolonging the cycle time. Therefore, the number of steps is similar to that of FIG. 7, but each step is more square and therefore darker. By combining the change in the number of steps in the cycle with the stop, typically 13 db excluding the effect of the stop.
The illuminance is further reduced by 13 db due to the effect of the shutdown.

An alternative method of dimming to providing a scanning stop period is to insert a simple filter into the light path after dimming from nine points to one continuous line. Once the filter is inserted,
The projection head projects 9 points again, and after that stage 1
Proceed to the book continuous line stage and repeat the series of dimming stages with the filter inserted.

The embodiments described above are to be used when there are either of two criteria that make it necessary to separate the light source from the projection head. That is, the space Kfl! in the cockbit! It should be used when there is a limit or when there is a restriction that the light source must be mounted flexibly. However, if these limitations do not exist, it is preferable to integrate the light source and projection head. As shown in FIG. 9, such a structure corresponds generally to that of FIG. 3, but with the exception that light from a spaced-apart source is incident at the location of reference numeral 52 (FIG. 3). A laser light source 90 is integrally provided that projects light onto a mirror 92 that directs the light toward the first mirror of the two @94.96. These mirrors cooperate with a scanning mechanism 98.100 which operates in a similar manner to that of the previous embodiment.

[Brief explanation of the drawing]

FIG. 1 shows two positions of a ray projected in front of one pilot according to the invention in the cockpit of an aircraft. FIG. 2 is a perspective view showing the physical relationship between the main parts of a preferred embodiment of the artificial horizon of the present invention. FIG. 3 is a sectional view of the projection head. Figures (a) to (f) of FIG. 4 are diagrams showing the positions of the rays with respect to the reference points, respectively. FIG. 5 is an enlarged progressive view showing the end connection of the optical AM. FIG. 6 is a schematic diagram showing a control circuit forming a part of the artificial horizon of the present invention. FIG. 7 is a graph illustrating the control signals for producing the desired streaks of bright light spots. FIG. 8 is a diagram illustrating other control signals in a similar manner to FIG. FIG. 9 shows another embodiment of the invention in a similar manner to FIG. Explanation of symbols of main parts 36...Projection head 38.90...Laser light source 40...Flexible connecting member 54.56, 92, 94, 96, River...Mirror 60 .66.
98,100... Scanning mechanism 76... Lens system 86... 1 person other than optical fiber

Claims (1)

[Scope of Claims] (1) An artificial horizontal image used to project a continuous visual representation of the true horizon in front of an aircraft pilot, comprising: a light source generating a light beam; a first reflective member movable about a first axis for causing said light beam to scan generally in a first plane;
a second reflective member movable about a second axis for causing light coming from the first reflective member to be scanned in a second plane that is generally perpendicular to the first plane; a scanning means provided in the path of the light beam for forming an image which should be recognized by the pilot as a light streak present in a position representing horizontal flight; In response to a coupled signal coming from an aircraft gyroscope, the rays rotate to deflect the first and second reflective members such that they roll and move vertically to indicate pitching. An artificial horizontal image comprising control means for causing the rotation of the first and second axes to move, and wherein the rays represent the true horizon regardless of the orientation of the aircraft. (No. 211, the first and second reflective members are each flat (8)
Claim 1: An artificial horizontal image of a first cage arrangement ridge, which is a key. (3) A patent characterized in that the control means causes the first and second reflective members to vibrate in a stepwise manner, and the striations consist of a series of bright spots connected through a relatively dark area. An artificial horizontal image according to claim 1. (4) It includes a trap member arranged so as to block a part of the light projected from the drilling scanning means, and the 111 control hand wave prevents the scanner during each period of scanning of the pre-bC projection light. A period is set, and during the scanning stop period, the light beam is diverted by the trap member, and the scanning time of the Mu light distribution beam is set as a short axis. The illuminance of the light streaks generated by
The artificial horizontal value according to claim 1g4. (5) further comprising means for varying the 5 degree angle of the image perceived by the pilot; fF;
Artificial horizontal value based on the first term of the range of itlI search. (6) The light source includes a racer light source and a single optical fiber;
The source coming from said racer light source? a means for converging the light to the incident end of the optical fiber; and a means for paralleling the light to be coupled to the opposite end of the optical fiber and radiate from the optical fiber. An artificial horizontal value according to claim 1, characterized in that it comprises means for forming a beam. (7) Artificial horizontal value used to project a ray in front of the aircraft pilot that visually differs from the true horizontal plane (low + 7f of the aircraft's gyroscope). The information output is received and the output from the lever is converted into two waveforms that are in phase under the first condition and have a phase difference of 180° from each other under the second condition.
9, the first rolling output of the two rolling outputs is a function of the cosine of the instantaneous rolling angle of the instantaneous rolling angle. 1) The outputs of the second output having a certain value are a function of the sine of the instantaneous rolling angle, and the composite plot of these outputs forms a constant straight line with respect to the reference edge, the rolling angle t - the instantaneous rolling angle. The direct mounting has a positive /l-j distribution under the first condition and a negative distribution M under the second condition; a second means for converting the lever output into a pitch output that is directly proportional to the bitching angle; a first composite output having a temporary value that is a function of the sum of the transverse of the sine of the angle; and a temporary value that is a function of the sum of the second rolling output and the pitching output and the transverse of the cosine of the rolling angle. a mixing means for generating a second combined output having a light beam; a light source for generating a light beam; and first and second mirror means disposed to vibrate about respective reference points. , the said structure means is MIJ entry 1 2 failure output? The punishing light beam is reflected and deflected by about 90 degrees by the first mirror means, and the reflected and deflected light beam is rotated by about 90 degrees by the second mirror means,
An artificial horizon whose mission is that the two mirror means work together to project a ray at a position corresponding to the horizon with respect to a reference point, regardless of the orientation of the aircraft. (8J) The light source that generates the beam is a laser beam @T'5r: Artificial horizontal plane in Section 1 of Claim 7. : Motobuta, who was born as an older brother, was said to be in the Kusumi group, and the light that was born to Sir Kugen as an older brother was si.
Sennari concentrates on one end of the 9-character embroidery rut in the J-ki, and the 9-dispersion source that shined from the other end of the 9-character fiber from the previous day is turned into parallel light, and the light enters the current means on the 6th side of the eye. A claim characterized in that it includes a raw plate forming a heel.
f; f' is the artificial horizontal value described in the range of 7th item. (11) A trap member is arranged so as to suppress a moment of light projected from the current means of +iii Note 2, and the control means stops scanning in the darkness of the scanning of the projection. Due to the period, the race was 11j in the same circle.
The recording beam is projected onto the back of the trap raider, and during the trapping, the running time is on the short axis, so the front b [-
Low illuminance in one light beam to produce an image fc
Artificial horizontal rice with special IFt Tsumugi ice range No. 7 rotation. (12) Touch market!・Claim 1 is characterized in that it produces a stepwise vibrational movement of the key means of Gojudan II Pre-retirement 1 and Funeral 2, and is composed of bright spots that are connected to the light streak through a comparatively dark area. Artificial horizontal instrument described in Section 7. (13) An artificial horizon, which can be moved along the first axis to project a VC projection in front of the pilot of the aircraft, to provide a continuous visual indication of true leveling. Tehot
With the key means arranged to deflect the light with respect to the eaves of the younger brother 1; moving to the second female turn, MIJm detects the source coming from the key means of the younger brother 1. The millet is deflected about a second axis that is at 90° with respect to the first axis. The light emitted from said second key means is configured to be moved along a predetermined path; Originally, it was characterized by having a control stage for moving the key means so as to scan a line representing the true horizon with a wave number large enough for the pilot to perceive the entire beam. (14) Said means provide a forward light distribution to perform a series of fast and slow movements so that the pilot perceives one bright area along said beam separated by a tI zone of very low illumination. 12. The artificial horizon according to claim 11, wherein the % sign is to repeatedly scan the front 8e line.