CN108791943B - Landing guiding system and landing guiding method for aircraft horizontal flight path landing mode - Google Patents
Landing guiding system and landing guiding method for aircraft horizontal flight path landing mode Download PDFInfo
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- CN108791943B CN108791943B CN201810746317.8A CN201810746317A CN108791943B CN 108791943 B CN108791943 B CN 108791943B CN 201810746317 A CN201810746317 A CN 201810746317A CN 108791943 B CN108791943 B CN 108791943B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/18—Visual or acoustic landing aids
- B64F1/20—Arrangement of optical beacons
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/10—Simultaneous control of position or course in three dimensions
- G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
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Abstract
The invention discloses a landing guiding system and a landing guiding method for an airplane horizontal flight path landing mode, wherein the landing guiding system comprises a green signal lamp, an orange signal lamp, a red signal lamp and a distance meter which are arranged on a ship deck; the green signal lamp is arranged at the tail of a deck of a ship, the orange signal lamp, the red signal lamp, the distance meter and the green signal lamp are sequentially arranged on the deck, the distance meter is electrically connected with the red signal lamp through a controller, and the landing point of the airplane is between the green signal lamp and the orange signal lamp. According to the invention, by providing the flight path of the aircraft landing ship which is easier to operate and guiding the landing system by the horizontal flight path landing mode of the aircraft, the difficulty coefficient of aircraft landing is reduced, the physical strength and energy of a pilot are reduced, the psychological pressure and operation difficulty borne by the pilot are reduced, and the improvement of the flight quality and the improvement of the flight safety factor are facilitated.
Description
Technical Field
The invention relates to the technical field of airplane landing guiding, in particular to a landing guiding system and method in an airplane horizontal flight path landing mode.
Background
The existing flight mode of landing an airplane on a ship lands on a slow descent flight path with an included angle of 4 degrees with the sea level, and the ship in constant-speed pursuit navigation finally lands on a deck of the ship. In the process of chasing and slowly landing, a guiding device combined by Fresnel lenses is used, and the airplane realizes the slow landing with an included angle along a parallel light beam channel given by the Fresnel lenses.
In the process, as the landing process is long and the flight path is inclined, the flight difficulty is high, a pilot needs to concentrate on energy, more physical power and energy are paid, the borne psychological pressure is high, and the difficulty coefficient of flight safety is high.
Disclosure of Invention
The invention aims to provide a landing guiding system and a landing guiding method for an aircraft horizontal flight path landing mode, which are used for solving the problems in the prior art, reducing the difficulty coefficient of aircraft landing ships and improving the flight safety coefficient.
In order to achieve the purpose, the invention provides the following scheme:
the invention provides a landing guiding system in an airplane horizontal flight path landing mode, which comprises a green signal lamp, an orange signal lamp, a red signal lamp and a distance meter, wherein the green signal lamp, the orange signal lamp, the red signal lamp and the distance meter are arranged on a ship deck;
the green signal lamp sets up the afterbody on deck, orange signal lamp, red signal lamp with the distancer with the green signal lamp sets gradually on the deck, the distancer through a controller with the red signal lamp electricity is connected.
Preferably, the flight control system further comprises a projection device arranged in the airplane, and the projection device can display the projection line of the current flight path and the airplane flight parameters on a front window of the airplane.
Preferably, the projection line of the current track is a corrected track projection line.
Preferably, the projection device is replaced by a helmet-mounted display device.
Preferably, the orange signal lamp is arranged in the middle of the deck, and the red signal lamp and the range finder are arranged in the front of the deck and face the rear without shielding.
Preferably, the green signal light and the orange signal light are spaced at a vertical height of 2m-5 m.
Preferably, the green signal lamp and the orange signal lamp are arranged on a longitudinal central axis of the ship in the sailing direction.
Preferably, the starting position of the aircraft entering the landing preparation phase is at least 1100m from the stern of said vessel.
Preferably, the horizontal flight path of the aircraft has a flight height of 20m-60m relative to the deck.
The invention also provides a landing guiding method of the aircraft horizontal flight path landing mode, the aircraft finds the ship in uniform speed straight line navigation, after the direction is roughly determined, the aircraft enters a landing preparation stage along the horizontal flight path, a pilot adjusts the course at any time in the horizontal flight path, when a green signal lamp and an orange signal lamp are positioned on the projection line of the current flight path of the aircraft, the aircraft aligns to a landing channel on a deck, the flight height and the flight speed are kept unchanged, and the aircraft tracks and approaches the ship;
the landing critical point of the airplane is point A, when the airplane flies to the point A, the distance meter monitors that the airplane and the ship reach a set distance, the controller sends an instruction to enable the red signal lamp to be turned on, and after the pilot sees that the red signal lamp is turned on, the pilot immediately operates the airplane to descend the airplane at a specified descent rate for one time to enable the airplane to land on a deck of the ship, and the tail hook of the airplane is enabled to hang the arresting cable, so that the landing in the horizontal landing mode of the airplane is completed.
Compared with the prior art, the invention has the following technical effects:
according to the invention, by providing the flight path of the aircraft landing ship which is easier to operate and guiding the landing system by the horizontal flight path landing mode of the aircraft, the difficulty coefficient of aircraft landing is reduced, the physical strength and energy of a pilot are reduced, the psychological pressure and operation difficulty borne by the pilot are reduced, and the improvement of the flight quality and the improvement of the flight safety factor are facilitated.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a landing guidance system for an aircraft horizontal flight path landing mode according to the present invention;
FIG. 2 is a schematic illustration of the nose window display data of the aircraft of the present invention as it lands;
wherein: 1-ship, 2-deck, 3-plane, 4-sea level, 5-green signal light, 6-orange signal light, 7-red signal light, 8-range finder, 9-descent flight path, 10-horizontal flight path, 11-flight parameter, 12-projection line of current flight path.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without inventive effort based on the embodiments of the present invention, are within the scope of the present invention.
The invention aims to provide a landing guiding system and a landing guiding method for an aircraft horizontal flight path landing mode, which are used for solving the problems in the prior art, reducing the difficulty coefficient of aircraft landing ships and improving the flight safety coefficient.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
As shown in fig. 1 to 2: the embodiment provides a landing guiding system in an airplane horizontal flight path landing mode, which comprises a green signal lamp 5, an orange signal lamp 6, a red signal lamp 7 and a range finder 8 which are arranged on a deck 2 of a ship 1.
The landing point of the aircraft 3 is between the green signal light 5 and the orange signal light 6. Wherein the angle of inclination of the descent trajectory 9 of the aircraft 3 is 4 °. The green signal lamp 5 and the orange signal lamp 6 are arranged on the central axis of the ship 1 in the longitudinal direction of sailing, so that the transverse swinging and the longitudinal swinging of the ship 1 basically do not affect the indicating function of the longitudinal direction of the signal lamp, and the requirement of the stability of each signal lamp can be met without being arranged on an inertial stabilization holder in the embodiment.
The flight control system further comprises a projection device arranged in the airplane 3, wherein the projection device can display the projection line 12 of the current flight path, the flying parameters 11 such as the flying height and the flying speed of the airplane 3 and the like on the front window of the airplane 3, and the projection line 12 of the current flight path is the corrected flight path projection line. The pilot can see the flight path projection line and the flight parameters 11 without influencing the sight, and can observe the scenes in front of and around the airplane 3 at any time. The projection device can be replaced by a helmet display device, the helmet display device can also display the projection line 12 of the current flight path, the flying parameters 11 such as the flying height and speed of the airplane 3, and the green signal lamp 5 and the orange signal lamp 6 observed in front can fall in the helmet display.
Usually, the landing passage of the airplane 3 on the ship 1 is not exactly located on the central axis of the ship 1, but has a certain transverse position deviation, so when the projection device displays the projection line 12 of the current flight path, a corresponding correction needs to be made, so that the pilot still only needs to make the green signal lamp 5 and the orange signal lamp 6 simultaneously fall on the flight path projection line, the alignment of the airplane 3 and the landing passage can be calibrated, and the alignment of the airplane 3 and the landing passage in the landing process is facilitated.
The initial position of the aircraft 3 entering the landing preparation phase is at least 1100m away from the tail of the ship sailing at a constant speed. The distance of the aircraft 3 entering the landing preparation stage needs to be selected according to the model of the aircraft 3, and the faster the flight speed is, the greater the distance of the aircraft entering the landing preparation stage is.
The horizontal flight path 10 of the aircraft 3 has a flight height of 20m-60m relative to the deck 2. The flying height of the horizontal track 10 of the airplane 3 relative to the deck 2 needs to be selected according to the length of the ship 1, the longitudinal swing degree correspondingly generated and the model of the airplane 3, the larger the amplitude of the ship stern uplifted by the longitudinal swing of the ship 1 is, the faster the speed of the airplane 3 is, the higher the flying height of the horizontal track 10 relative to the deck 2 is, the higher the distance between the airplane 3 and the sea level 4 is, and conversely, the lower the distance between the airplane 3 and the sea level 4 is.
The embodiment also provides a landing guiding method of the airplane horizontal track landing mode, wherein the airplane 3 searches for the ship 1 in constant speed navigation, after the direction is roughly determined, the airplane 3 enters a landing preparation stage along the horizontal track 10, a pilot adjusts the heading in the horizontal track 10 at any time, and when the green signal lamp 5 and the orange signal lamp 6 are both positioned on the projection line 12 of the current track of the airplane 3, the airplane 3 is aligned to the landing passage on the deck 2, the flying height and the flying speed are kept unchanged, and the airplane tracks and approaches the ship 1.
The descending critical point of the airplane is point A, when the airplane flies to the point A, the distance meter 8 monitors that the airplane 3 and the ship 1 reach a set distance, the controller sends an instruction to enable the red signal lamp 7 to be turned on, and after the pilot sees that the red signal lamp 7 is turned on, the pilot immediately operates the airplane 3 to descend the airplane 3 at one time according to a specified descending rate, so that the airplane 3 lands on the deck 2 of the ship 1, the tail hook of the airplane 3 is hung on the stopping cable, and the landing of the airplane 3 in a horizontal landing mode is completed. Wherein the route from point a to deck 2 is descending route 9.
The flight mode of the airplane 3 in the landing preparation phase is a horizontal flight mode with fixed direction, fixed height and fixed speed according to the airplane type 3, and under the data monitoring and guidance of the landing guiding system of the airplane 3 horizontal track 10 landing mode in the embodiment, when the airplane 3 in the horizontal flight preparation phase reaches a descent critical point A, the airplane descends once and lands on the ship 1.
The principle and the implementation mode of the present invention are explained by applying specific examples in the present specification, and the above descriptions of the examples are only used to help understanding the method and the core idea of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (9)
1. A landing guiding system in an aircraft horizontal flight path landing mode is characterized in that: the device comprises a green signal lamp, an orange signal lamp, a red signal lamp and a distance meter which are arranged on a ship deck;
the green signal lamp is arranged at the tail part of the deck, the orange signal lamp, the red signal lamp, the distance meter and the green signal lamp are sequentially arranged on the deck, and the distance meter is electrically connected with the red signal lamp through a controller;
the flight height of the horizontal flight path of the airplane relative to the deck is 20m-60 m.
2. The aircraft horizontal flight path landing pattern guided landing system of claim 1, wherein: the aircraft flight control system further comprises a projection device arranged in the aircraft, and the projection device can display the projection line of the current flight path and the aircraft flight parameters on a front window of the aircraft.
3. The aircraft horizontal flight path landing pattern guided landing system of claim 2, wherein: and the projection line of the current track is the corrected track projection line.
4. The aircraft horizontal flight path landing pattern guided landing system of claim 3, wherein: the projection device is replaced by a helmet display device.
5. The aircraft horizontal flight path landing pattern guided landing system of claim 1, wherein: the orange signal lamp is arranged in the middle of the deck, and the red signal lamp and the range finder are arranged in the front of the deck and face the rear without shielding.
6. The aircraft horizontal flight path landing pattern guided landing system of claim 1, wherein: the green signal lamp and the orange signal lamp are spaced at a vertical height of 2m-5 m.
7. The aircraft horizontal flight path landing pattern guided landing system of claim 1, wherein: the green signal lamp and the orange signal lamp are arranged on a longitudinal central axis of the ship in the sailing direction.
8. The aircraft horizontal flight path landing pattern guided landing system of claim 1, wherein: the starting position of the aircraft entering the landing preparation phase is at least 1100m from the stern of the ship.
9. The landing guiding method of the landing guiding system based on the aircraft horizontal flight path landing pattern of any one of claims 1 to 8, characterized by comprising the following steps:
the aircraft finds a ship in uniform-speed straight line navigation, after the direction is roughly determined, the aircraft enters a landing preparation stage along a horizontal track, a pilot adjusts the course at any time in the horizontal track, and when a green signal lamp and an orange signal lamp are both positioned on a projection line of the current track of the aircraft, the aircraft aligns to a landing channel on a deck, the flying height and the flying speed are kept unchanged, and the aircraft tracks and approaches the ship;
the landing critical point of the airplane is point A, when the airplane flies to the point A, the distance meter monitors that the airplane and the ship reach a set distance, the controller sends an instruction to enable the red signal lamp to be turned on, and after the pilot sees that the red signal lamp is turned on, the pilot immediately operates the airplane to descend the airplane at a specified descent rate for one time to enable the airplane to land on a deck of the ship, and the tail hook of the airplane is enabled to hang the arresting cable, so that the landing in the horizontal landing mode of the airplane is completed.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810746317.8A CN108791943B (en) | 2018-07-09 | 2018-07-09 | Landing guiding system and landing guiding method for aircraft horizontal flight path landing mode |
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| CN201810746317.8A CN108791943B (en) | 2018-07-09 | 2018-07-09 | Landing guiding system and landing guiding method for aircraft horizontal flight path landing mode |
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| CN108791943B true CN108791943B (en) | 2020-05-08 |
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| CN109896014B (en) * | 2019-03-28 | 2022-11-18 | 徐州臣赐网络科技有限公司 | Fixed-wing unmanned aerial vehicle roof airdrop indicating method |
| CN111210668B (en) * | 2019-12-30 | 2022-02-15 | 四川函钛科技有限公司 | Landing stage flight trajectory offset correction method based on time sequence QAR parameter |
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| DE102009043534A1 (en) * | 2009-09-30 | 2011-04-07 | Adb Bvba | Firing unit for airfield lighting |
| BR112013003760B1 (en) * | 2010-08-19 | 2020-12-08 | Scott P. Stauffer | traffic limit / edge marker that integrates a set of limit / edge markers for vehicle traffic on the ground |
| CN105539868B (en) * | 2015-12-25 | 2017-08-25 | 中国航空工业集团公司北京航空制造工程研究所 | Above-decks equipment, airborne equipment, guide device and the method for warship for aircraft |
| CN205366055U (en) * | 2015-12-31 | 2016-07-06 | 歌尔科技有限公司 | Unmanned aerial vehicle control system that rises and falls |
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