RU2483986C2 - Aircraft landing system - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates aviation, particularly to aircraft landing systems and is intended to provide visual spatial pilot orientation when approaching to landing in conditions of limited visibility. The system generates glideslope beams providing individual AC descending trajectories depending on cockpit height relative to lower point of chassis or arresting hook. The aircraft landing system contains left and right laser emitters and corresponding shapers of glideslope beams spatial position at an angle to runway (RW) plane located along edges of RW and is provided with right and left devices respectively to move shapers with possibility of their fixation at distance d to RW threshold which is functionally connected with cab height relative to lower point of chassis or arresting hook (h) and with height oat which aircraft crosses RW threshold (h_thr). Calculations of shapers fixation place coordinates before landing of specific aircraft and generation of control commands for shaper moving devices are performed by central processor of flight control system.

EFFECT: higher control accuracy and flight safety.

10 cl, 5 dwg

Description

The invention relates to aviation systems and can be used in the light-signal equipment of aerodromes and landing sites of aircraft carriers to visualize the descent trajectory, which allows the pilot of a particular type of aircraft to cross the runway threshold at the calculated (set) height and touch the landing gear of the aircraft landing gear or to catch the cable the aerofinisher at a given point (for example, one point for all types of aircraft).

The known optical system [1] (Pavlenko VF Ship aircraft. - M .: Voenizdat, 1990. - Pages 259-261) for the exact landing of aircraft on the deck of the ship, which consists of light-signal indicators mounted on the side of the runway of various colors and radiation patterns, from the light-signaling information from which the pilot determines the position of the aircraft relative to a given descent path. To perform an aircraft landing, having differences in the height of the cockpit relative to the chassis, the system has a device for turning light-signal indicators in the plane of the transverse descent path. When the light-signal indicators are turned, the specified angle of indication of the aircraft descent trajectory is saved and the height of the light zones is shifted - indicators of the aircraft descent glide path, which allows the pilot to land the aircraft having differences in the height of the cockpit relative to the brake hook or lower point of the landing gear and ensure that brake hook of aerial wire rope aerofinisher.

The disadvantage of the optical system [1] is the effect of reducing the accuracy of aircraft landing on the deck of the ship due to a change in the indication of the threshold altitude of the runway threshold in case of aircraft drift relative to the course during the approach, which is unsafe for landing on runways with limited dimensions. In addition, due to the significant dynamic and mass-dimensional characteristics of the optical system, the adaptation time and operational control of the optical system during the approach of various types of aircraft are increasing.

A technical solution is known [2] (Zuev V.E., Fadeev V.Y. Laser navigation devices. - M .: Radio and communications, 1987. - Page 89), containing three laser emitters installed at the beginning of the runway, two of which located at the edges, and a third on the longitudinal axis of the runway. This system with the help of laser beams forms linear landmarks in space, along which the pilot performs the descent and landing of the aircraft near the calculated touchdown point.

The disadvantage of the technical solution [2] is that when oriented according to the known landing system, the touch of the runway occurs at different distances from the threshold of the runway for aircraft, with differences in the height of the cockpit relative to the lower point of the landing gear in the approach mode, which is unsafe for short runways and especially when landing on the deck of an aircraft carrier ship.

The closest technical solution is a laser aircraft landing system [3] (RF patent No. 2369532, IPC B64F 1/18), which contains three laser emitters installed near the runway from the side of the aircraft’s approach, two of which are left and the right - glide path - located at the edges of the strip at a fixed distance d ₀ from the beginning of the strip.

The disadvantage of this technical solution [3] is the fixed position of the emitters relative to the threshold of the runway, which does not allow aircraft pilots with differences in cabin height relative to the bottom point of the landing gear or brake hook to visually indicate the aircraft's descent path to land at the calculated point of the landing strip, for example, to ensure that the LA brake hook grabs the aerofinisher cable.

The aim of the invention is the formation of glide path rays that provide individual (calculated) aircraft flight paths that differ in the height of the cockpit relative to the lower point of the landing gear or brake hook and, as a result, the aircraft landing gear is touched or the brake cable grabs the aerofinisher cable at a given point of the runway at landing aircraft.

This goal is achieved by the fact that the left and right laser emitters located at the edges of the runway, for example laser emitters with optical formers of spatial position of glide paths, are made with the possibility of remote movement parallel to the runway axis and fixing them at a distance d from the runway threshold, which is functional associated with the height of the cockpit of a particular type of aircraft approaching, relative to the lower point of the landing gear or brake hook. At the same time, the pilot of the aircraft, visually guided by the glide path, ensures that the landing gear cable touches the landing gear or the brake hook of the aircraft at the given point of the runway.

The aircraft landing system differs from the well-known technical solution, containing at least the left and right laser emitters and the corresponding left and right shapers of the spatial position of the glide paths at an angle located at the edges of the runway (runway) from the side of the aircraft approaching φ to the plane of the runway in that the landing system is additionally equipped with a left and right device for moving the formers of the spatial position of the glide paths with the possibility of fixing their distance at a distance d from the threshold of the runway, which is functionally related to the height h of the cockpit relative to the lower point of the landing gear or brake hook and the height h of _the intersection of the threshold of the runway threshold with an aircraft of type Si

d _i = (h _then + h _i ) tgφ.

Besides:

- the formers of the spatial position of the glide path rays are made in the form of a wedge-shaped transparent plate with a wedge angle α in the vertical plane for a small angle equal to [4]:

α = φ / (n-1)

or in general terms

α = arctan [Sinφ / (n-Cosφ)],

where α is the angle of the wedge of the plate,

n is the refractive index of the plate material,

φ is the glide path angle;

- the shapers of the spatial position of the glide path rays are made in the form of m-pairs, each of which consists of the right fm and left fm * shaper

(right - f1, f2, ... fi, ... fm; left - f1 *, f2 *, ... fi *, ... fm *) and installed at distances d1, d2 ... di ... dm from the runway threshold in accordance with the expression d _i = (h _then + h _i ) tan φ;

 - on the optical surface of the plate a transparent conductive coating is applied, connected to a power source and a device for monitoring and controlling the temperature of the plate with the ability to maintain the temperature of the plate above the dew point.

 - the optical surface of the plate is made with a coating on the wavelength of the laser emitter;

- calculations of the coordinates of the fixation point of the formers of the spatial position of the glide paths according to the formula d _i = (h _por + h _i ) tgφ for an aircraft of type Si and the formation of control commands is carried out by the central processor of the flight control system.

The invention is illustrated by drawings of figure 1 (a, b), figure 2, figure 3, figure 4 and figure 5.

In FIG. 1 (a, b), FIG. Figure 2 shows the arrangement of laser emitters and formers of spatial position of glide paths mounted on devices for moving the formers parallel to the axis of the runway, as well as the position in space relative to the plane of the runway of the rays of laser emitters and glide path laser beams for two types of aircraft, characterized by the height of the pilot cabin relative to the chassis points. Figure 3 - shows the optical shaper spatial position of the glide path in the form of a wedge-shaped transparent plate.

In FIG. 4 and FIG. Figure 5 shows a variant of the system for landing aircraft on the runway, for example, on the landing pad of an aircraft carrier using m-pairs of glider path shapers, including right shapers fm and left fm * installed along the edges of the runway (runway) with sides of the aircraft landing approach,

In Fig.1 (a, b), Fig. 2, FIG. 3, FIG. 4 and FIG. 5 adopted the following conventions:

1, 1 ^* - right and left laser emitters;

2, 2 ^* - beams of laser emitters;

3, 3 ^* - formers of spatial position of glide path rays;

4, 4 ^* - a device for moving and fixing the formers of the spatial position of glide paths;

5, 5 ^* - glide path rays (example for an aircraft of type S ₁ pos. 7);

6 - the trajectory of the lower point of the landing gear or brake hook of the aircraft;

7 - aircraft type S ₁ ; 8 - runway threshold; 9 - the touch point of the aircraft chassis (or brake hook) of the runway surface; 10, 10 ^* - glide path rays (example for an aircraft of type S _m pos. 11); 11 - aircraft type S _m ; 12, 12 * - the side boundaries of the runway; 13 - center line (axis) of the runway; 14 - wedge-shaped transparent plate; 15 - input face of the wedge-shaped plate; 16 - output face of the wedge-shaped plate; 17 - the geometric axis of the wedge-shaped plate; φ is the glide path angle; h _then - the specified height of the intersection of the threshold of the runway; h ₁ - the distance from the cab to the lower point of the chassis wheels (example for LA 7 type S ₁ ); h _m is the distance from the cab to the lower point of the chassis wheels (example for LA 11 type S _m ); d _1, d _{2, ...} d _{i, ...} d _m - distance from the runway threshold to the place of fixation of the formers of the spatial position of the glide path for various types of aircraft (S _1, S _{2 ...} S _{i ...} S _m );

f1, f1 *; f2, f2 *; ... fi, fi *; ... fm fm *) - right (fi) and left (fi *) shapers, a priori mounted at distances d1, d2, ... di, ... dm with the possibility of introducing glide path rays into the formation mode for the corresponding aircraft types (S1, S2 ... Si ... Sm).

The formation of the glide path for a specific type of aircraft will be considered using the example shown in Fig. 1a (an example for an aircraft of type S ₁ pos. ₇ , h ₁ ). Before approaching the aircraft pos.7 with the height of the cockpit relative to the lower point of the landing gear h ₁ , the glide path position control system calculates the distance d ₁ from the threshold of runway 8 to the fixation point of the formers of the spatial position of the glide paths using the formula d ₁ = (h _por + h ₁ ) tgφ and generates control signals. Moving devices 4 and 4 * under the influence of control commands remotely install and fix the shapers 3 and 3 * at the estimated distance d ₁ from the threshold of the runway. Laser beams 2 and 2 * of the right and left emitters 1 and 1 *, passing through the shapers 3 and 3 *, made in the form of a wedge-shaped transparent plate with input and output faces (Fig.3 pos. 14, 15, 16, 17), are rejected at an angle φ, forming the right 5 and left 5 * glide path rays. Aircraft pilot (pos. 7), visually orienting along the formed glide path, provides the trajectory of the lower point of the aircraft landing gear along line 6 and touching the aircraft landing gear to the runway surface at point 9.

The process of forming a glide path (Fig. 1 (b), Fig. 2) for an aircraft with a height h _{m of the} cockpit relative to the lower point of the landing gear (example for an aircraft of type S _m pos. 11, h _m <h ₁ ) is similar to the formation of a glide path for LA type S ₁ pos.7 figa. and it doesn’t fundamentally differ from the described example, except that before the aircraft approach pos. 11 with the height of the cockpit relative to the lower point of the landing gear h _m , the glide path position control system calculates the distance d _m from the threshold of runway 8 to the fixation point of the spatial formers glide path position using the formula d _m = (h _then + h _m ) tgφ and generates glide path formation signals for the aircraft S _m . Aircraft pilot pos. 11, visually guided by the formed glide path (glide path 10.10 *), provides the movement of the lower point of the aircraft chassis along trajectory 6, i.e. along the same trajectory as for the case of landing the aircraft pos.7, and, accordingly, the touch of the aircraft chassis pos.11 of the runway surface occurs at point 9.

Formation of aircraft glide slope in landing system (4; 5) using m-pairs (Q-1, Q-1 ^*, Q2, Q2 ^*; ... .phi.i, .phi.i; ^* ... * the FM the FM right and left [*]) formers spatial position glide path rays, carried out by one of the pairs fi, fi * for Si-type aircraft. Shapers of the spatial position of glide path rays are a priori installed at fixed distances d ₁ , d ₂ ... d _i ... d _m from the runway threshold, calculated by the formula d _i = (h _pores + h _i ) tgφ in accordance with the parameters h ₁ , h ₂ ... h _i ... h _m aircraft S ₁ , S ₂ ... S _i ... S _m types and in the initial state do not interact with the beams of laser emitters 2,2 *. The required glide path for the exact landing of a specific aircraft, for example, for the exact landing of aircraft on the deck of a ship with the brake hook of the aircraft holding the aerofinisher cable at one point for all types of aircraft, is formed by a command from the control system for automatically introducing the appropriate pair of shapers into the laser beam. Aircraft pilot (pos. 7), visually guided by the formed glide path (glide paths 5, 5 *), provides the trajectory of the lower point of the aircraft landing gear along line 6 and touching the aircraft landing gear to the surface of the runway at point 9.

Information sources

1. Pavlenko V.F. Ship aircraft. - M .: Military Publishing House, 1990. - Page 259-261.

2. Zuev V.E., Fadeev V.Ya. Laser navigation devices. - M .: Radio and communications, 1987. - Page 89

3. RF patent No. 2369532, IPC B64F 1/18.

4. Reference designer of optical-mechanical devices. Under the total. ed. V.A. Panova. 3rd ed., Revised. and add. - L .: Engineering, Leningrad. Department, 1980 .-- 742 p.

Claims (10)

1. Aircraft landing system, comprising at least right and left laser emitters and corresponding shapers of the spatial position of the glide path rays at an angle φ to the plane of the runway, located at the edges of the runway (runway) from the aircraft approaching side, characterized in further provided respectively right and left displacement devices formers spatial position glide beams with the possibility of fixing them at a distance d _i to a threshold, which functional- connected with the cabin height h _i pilot arrangement aircraft S _i relative to the lower chassis or the braking point and the height h of the hook aircraft runway threshold crossing _far ratio d _i = (h _then + h _i) tgφ. 2. The aircraft landing system according to claim 1, characterized in that the formers of the spatial position of the glide paths are made in the form of a wedge-shaped transparent plate with a wedge angle α in the vertical plane equal to
α = arctan [Sinφ / (n-Cosφ)],
where α is the angle of the wedge of the plate;
n is the refractive index of the plate material;
φ is the glide path angle. 3. The aircraft landing system according to claim 2, characterized in that a transparent conductive coating is applied to the optical surfaces of the wedge-shaped transparent plate, connected to a power source and a plate temperature control and regulation device with the ability to maintain the plate temperature above the dew point temperature. 4. The aircraft landing system according to claim 2, characterized in that the optical surfaces of the wedge-shaped transparent plate are made with an antireflection coating at the wavelength of the laser emitter. 5. The aircraft landing system according to claim 1, characterized in that the calculation of the fixation point d _i for the spatial position of the glide path rays and the formation of control commands are carried out by the central processor of the flight control system. 6. Aircraft landing system, comprising at least right and left laser emitters and corresponding shapers of the spatial position of the glide path rays at an angle φ to the plane of the runway located at the edges of the runway (runway) from the side of the aircraft approaching
characterized in that the formers of the spatial position of the glide path rays are made in the form of m pairs of right and left [*] (ф1, ф1 *; ф2, ф2 *; ... фi, фi *; ... фm, фm *) formers with the possibility of entering into the formation mode glide rays and which are mounted at a distance d _i to a threshold that is operatively connected to the height h _i location S _i aircraft cockpit unit relative to the lower chassis points or braking hook and the altitude h of the aircraft runway threshold crossing _far ratio d _i = (h _then + h _i ) tgφ. 7. The aircraft landing system according to claim 6, characterized in that the formers of the spatial position of the glide paths are made in the form of a wedge-shaped transparent plate with a wedge angle α in the vertical plane equal to:
α = arctan [Sinφ / (n-Cosφ)],
where α is the angle of the wedge of the plate;
n is the refractive index of the plate material;
φ is the glide path angle. 8. The aircraft landing system according to claim 7, characterized in that a transparent conductive coating is applied to the optical surfaces of the wedge-shaped transparent plate, connected to a power source and a plate temperature control and regulation device with the ability to maintain the plate temperature above the dew point temperature. 9. The aircraft landing system according to claim 7, characterized in that the optical surfaces of the wedge-shaped transparent plate are made with an antireflective coating at the wavelength of the laser emitter. 10. The aircraft landing system according to claim 6, characterized in that the calculation of the installation location d _i for the spatial position of the glide path rays and the formation of control commands are carried out by the central processor of the flight control system.

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