Auxiliary landing system and method for helicopter under sand blind condition

Abstract

The invention relates to the technical field of helicopter landing, and discloses an auxiliary landing system and method for a helicopter under a sand blind condition, and the system comprises a plurality of height prediction layers. The plurality of height prediction layers are sequentially sleeved around the helicopter take-off and landing area to form an early warning area; and each height prediction layer is provided with a height mark. The method comprises the following steps: preliminarily searching a take-off and landing area, and preliminarily determining the take-off and landing area as a landing point; identifying a height mark on the outermost height prediction layer in the current visual field, and judging the initial height of the current helicopter from the ground based on the height mark; in the continuous descending process of the helicopter, identifying a height mark on a height prediction layer entering the view for the first time, and updating the current real-time height of the helicopter from the ground based on the height mark; after the height prediction layer of the innermost layer is recognized, the helicopter gets close to the ground and prepares to land. The technical problem that the helicopter is difficult to land under the sand blind condition can be solved.

Description

Technical Field

[0001] The present invention relates to the technical field of helicopter landing, and particularly to a helicopter assisted landing system and method under sand-blind conditions. Background Art

[0002] As an important aviation vehicle, a helicopter has unique application value under complex terrains and adverse weather conditions. However, when a helicopter lands on a sandy ground, it often faces the problem that the wind and sand are rolled up to block the pilot's line of sight, which poses a serious threat to flight safety. Especially in areas with more sand and dust such as deserts and gobi, when a helicopter lands, the airflow generated by the rotor will raise a large amount of sand and dust, forming a thick sand and dust cloud, seriously affecting the pilot's visual judgment ability and significantly increasing the landing difficulty.

[0003] Therefore, providing a helicopter assisted landing system and method under sand-blind conditions to guide the helicopter to land is a technical problem that needs to be solved urgently by those skilled in the art. Summary of the Invention

[0004] The present invention discloses a helicopter assisted landing system under sand-blind conditions to solve the technical problem of great difficulty in landing a helicopter under sand-blind conditions in related technologies.

[0005] To solve the above problems, the present invention adopts the following technical solutions: In a first aspect, the present invention discloses a helicopter assisted landing system under sand-blind conditions, including a plurality of height prediction layers, and the height prediction layers are used to predict the height of the helicopter from the ground during the landing process; The plurality of height prediction layers are sequentially sleeved around the helicopter takeoff and landing area to form a warning area; Each height prediction layer has a height mark, and along the direction from the outer edge to the center of the warning area, the height of the helicopter marked by the height mark from the ground gradually decreases.

[0006] In a second aspect, the present invention discloses a helicopter assisted landing method under sand-blind conditions, which is implemented based on the helicopter assisted landing system under sand-blind conditions in the first aspect. The method includes the following steps: Preliminarily search for the takeoff and landing area and initially determine the takeoff and landing area as the landing point; Identify the height mark on the outermost height prediction layer in the current field of view, and judge the initial height of the current helicopter from the ground based on the height mark; During the continuous descent of the helicopter, identify the height mark on the height prediction layer that first enters the field of view, and update the real-time height of the current helicopter from the ground based on the height mark; After identifying the innermost height prediction layer, the helicopter approaches the ground and prepares to land.

[0007] The technical solution adopted by the present invention can achieve the following beneficial effects: The helicopter assisted landing system under sand-blind conditions of the present application initially searches for the takeoff and landing area in the air, initially determines the takeoff and landing area as the landing point, identifies the height marks on the outermost height prediction layer in the current field of view, and determines the initial height of the current helicopter from the ground based on the height marks; during the continuous descent of the helicopter, it identifies the height marks on the height prediction layer that first enters the field of view, and updates the real-time height of the current helicopter from the ground based on the height marks; after identifying the innermost height prediction layer, the helicopter approaches the ground and prepares to land. By setting multiple height prediction layers with different sizes, the present invention reduces complex flight parameters to graph languages that can be intuitively analyzed, establishes a strong mapping relationship between the physical space and visual features, provides a clear visual reference for the pilot, helps it quickly judge the height and position of the helicopter, thereby effectively reducing the probability of ground contact accidents and significantly improving landing safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0009] Figure 1 is a schematic structural diagram of the helicopter assisted landing system under sand-blind conditions of the present invention; Figure 2 is a schematic diagram of the state of the helicopter of the present invention at different heights; Figure 3 is a top view of the helicopter assisted landing system under sand-blind conditions of the present invention; Figure 4 is an axonometric view of the calibration plate of the present invention; Figure 5 is Figure 4 an enlarged view of part A in

[0010] In the figure: 100 - height prediction layer, 110 - calibration plate, 111 - light-emitting mark, 112 - pattern mark, 113 - sand guide groove, 114 - fastener, 1141 - soil-breaking part, 1142 - groove; 200 - helicopter; 300 - takeoff and landing area. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0011] To make the objectives, technical solutions, and advantages of the present invention clearer, the technical solutions of the present invention will be described in detail below. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. All other implementation manners obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts fall within the scope protected by the present invention.

[0012] The terms "first", "second", etc. in the specification and claims of this application are used to distinguish similar objects, rather than to describe a specific order or sequence. It should be understood that such data can be interchanged under appropriate circumstances so that the embodiments of this application can be implemented in an order other than those illustrated or described here, and the objects distinguished by "first", "second", etc. are generally of the same type, and the number of objects is not limited. For example, the first object can be one or multiple. In addition, "and / or" in the specification and claims means at least one of the connected objects, and the character " / " generally indicates an "or" relationship between the associated objects before and after.

[0013] The inventor found during the actual operation process that when the helicopter 200 lands on a sandy dust ground, it often faces the problem that the wind and sand are rolled up to block the pilot's line of sight, which poses a serious threat to flight safety. Especially in areas with more sandy dust such as deserts and gobi, when the helicopter 200 lands, the airflow generated by the rotor will raise a large amount of sandy dust, forming a thick sandy dust cloud, seriously affecting the pilot's visual judgment ability and significantly increasing the landing difficulty. The traditional helicopter 200 landing assistance means mainly include visual landmarks, navigation systems, and ground assistance facilities, etc. However, in a strong wind and sand environment, these means are often difficult to fully play their roles. For example, visual landmarks are easily covered under the shelter of sandy dust, and it is difficult for the pilot to accurately judge the distance between the helicopter 200 and the ground; although the navigation system can provide certain altitude data, it lacks an intuitive visual reference and is difficult to meet the pilot's operation requirements in a complex environment. In addition, the existing ground assistance facilities are mostly designed for ordinary runways and are difficult to adapt to the special environment of the sandy dust ground.

[0014] The following combines the attached Figures 1 to 5 , and through specific embodiments and their application scenarios, a helicopter assisted landing system and method under sand blindness conditions provided by this application will be described in detail.

[0015] Some embodiments of this application provide a helicopter 200 assisted landing system under sand blindness conditions, as Figures 1 - 3 shown, including a plurality of altitude prediction layers 100.

[0016] Such as Figure 1 and Figure 2As shown, multiple height prediction layers 100 are sequentially sleeved around the takeoff and landing area 300 of the helicopter 200 to form a warning area. The pilot determines the initial height by visually observing the maximum visible height prediction layer 100. As the smaller layers come into view during descent, the height reference can be iteratively updated, such as Figure 2 As shown. Multiple height prediction layers 100 are sequentially sleeved around the takeoff and landing area 300 of the helicopter 200, which can also ensure that the pilot can continuously observe the position change of the calibration plate 110 during landing.

[0017] In this embodiment, the height prediction layer 100 can be circular, square, or other shapes, and this embodiment does not limit this.

[0018] Such as Figure 3 As shown, each height prediction layer 100 has height markings. The height markings are used to predict the height of the helicopter 200 from the ground during landing, reduce complex flight parameters to a graph language that can be intuitively analyzed, establish a strong mapping relationship between the physical space and visual features, provide a clear visual reference for the pilot, help them quickly judge the height and position of the helicopter 200, thereby effectively reducing the probability of ground contact accidents and significantly improving landing safety.

[0019] Such as Figures 1 - 3 As shown, along the direction from the outer edge to the center of the warning area, the height of the helicopter 200 marked by the height markings from the ground gradually decreases. The height markings of each height prediction layer 100 gradually decrease from the outside to the inside, reconstructing the space reference in extreme environments such as sand blindness, enabling the pilot to safely land without relying too much on electronic devices.

[0020] Such as Figure 1 And Figure 2 As shown, the radial dimension after multiple height prediction layers 100 are sleeved with each other is the same as the rotation area of the helicopter 200's rotor, ensuring that during the landing of the helicopter 200, the pilot can continuously observe the position change of the height prediction layer 100.

[0021] And / or, adjacent two height prediction layers 100 are arranged at intervals.

[0022] And / or, adjacent two height prediction layers 100 are arranged closely.

[0023] In some embodiments, any two adjacent height prediction layers 100 are arranged at intervals. Arranging any two adjacent height prediction layers 100 at intervals can form a larger circle coverage range, optimize the spatial perception accuracy by expanding the gradient density of the visual scale: the interval area allows each layer of height markings to independently occupy a larger visual field area, enabling the pilot to capture the warning signal of the outer height prediction layer 100 at a higher altitude and adjust the heading in advance.

[0024] In some embodiments, any two adjacent height prediction layers 100 are arranged closely. The close arrangement of any two adjacent height prediction layers 100 enables the formation of a visual contrast line between the adjacent two height prediction layers 100. During the descent of the helicopter 200, the visual contrast line can serve as a warning to the pilot, reminding the pilot to update the height reference. Moreover, the visual contrast line can also enable the pilot to determine whether the helicopter 200 is offset. If the helicopter 200 is offset, the visual contrast line seen by the pilot will appear broken or tilted, directly indicating the direction and magnitude of the offset, so as to facilitate the pilot to adjust the flight attitude of the helicopter 200.

[0025] In some embodiments, some adjacent two height prediction layers 100 are arranged at intervals, and some adjacent two height prediction layers 100 are arranged closely. With such an arrangement, the distance between adjacent two height prediction layers 100 can be freely adjusted according to the terrain undulation, which is suitable for laying in harsh environments such as deserts.

[0026] As Figure 3 shown, the height prediction layer 100 includes a plurality of calibration plates 110, and the plurality of calibration plates 110 are arranged at intervals along the extending direction of the height prediction layer 100. The height prediction layer 100 is formed by combining the plurality of calibration plates 110. During transportation, the plurality of calibration plates 110 can be stacked for transportation, saving space and being more convenient for transportation. During installation, the plurality of calibration plates 110 can freely adjust the distance and angle of the calibration plates 110 according to the terrain undulation, which is especially suitable for the rapid construction of a temporary landing field in harsh environments such as deserts. During maintenance, when any one calibration plate 110 is damaged, it can be replaced independently without overall disassembly and assembly, reducing the maintenance cost.

[0027] The plurality of calibration plates 110 are arranged at intervals, and the interval area between any two adjacent calibration plates 110 can serve as a dust accumulation buffer zone, thereby preventing the dust from accumulating too high and covering the calibration plates 110. At the same time, the interval area also serves as a passage for the pilot to enter or leave the helicopter 200, so as to prevent the pilot from stepping on the calibration plates 110, increasing the service life of the calibration plates 110. Moreover, the adjacent two calibration plates 110 are arranged at intervals, reducing the number of calibration plates 110 used while ensuring that the height prediction layer 100 can be formed, thereby reducing the cost.

[0028] Preferably in this embodiment, the distance between any two adjacent height prediction layers 100 is 2m - 5m. It goes without saying that the distance between any two adjacent height prediction layers 100 is not limited to 2m - 5m, and it can also be other lengths, which can be flexibly set according to the design requirements, and this embodiment does not make any limitations in this regard.

[0029] As Figure 3 and Figure 4As shown, each calibration board 110 of each height prediction layer 100 is respectively provided with a height mark, and the height of the helicopter 200 identified by the height marks on the multiple calibration boards 110 from the ground is the same. The multiple calibration boards 110 independently set height marks, and the system reliability is improved through segmented redundancy design. Each calibration board 110 is an independent information unit. When sand and dust obscure or there is local damage, the remaining calibration boards 110 can still reconstruct a complete spatial reference grid through other calibration boards 110. At the same time, the modular design allows the marking density to be dynamically adjusted according to the environment, and the maintenance cost is reduced through local replacement.

[0030] As Figure 3 and Figure 4 shown, the height mark includes a light-emitting identifier 111. The light-emitting identifier 111 penetrates environmental interference through an active optical signal, significantly improving the reliability and real-time performance of the warning system.

[0031] Preferably in this embodiment, the light-emitting identifier 111 is an LED lamp.

[0032] In this embodiment, a built-in battery is provided in the calibration board 110 to supply power to the multiple light-emitting identifiers 111. And, the built-in battery of the calibration board 110 can be charged in the forms of solar energy, wind-solar hybrid, and storage batteries based on the conditions of the use site.

[0033] As Figure 3 and Figure 4 shown, the light-emitting identifier 111 is one or more of numbers, graphics, and symbols. Specifically, there are multiple light-emitting identifiers 111, and the multiple light-emitting identifiers 111 form one or more of numbers, graphics, and symbols.

[0034] Preferably in this embodiment, the height identifier is an Arabic numeral formed by multiple light-emitting identifiers 111, thereby giving the most intuitive height judgment for the altitude layer where the pilot is located. For example, the height identifiers from the outermost layer to the innermost layer are 100, 80, 60, 40, 20 in sequence. It goes without saying that the height identifier can also be a letter, a Greek numeral, etc. formed by multiple light-emitting identifiers 111, and can be flexibly set according to the use requirements. This embodiment does not make a limitation in this regard.

[0035] The colors of the light emitted by the light-emitting identifiers 111 on each height prediction layer 100 are different. Through the height identification system with color differentiation, the pilot can quickly establish the association between the spatial position and the operation stage during the descent process, significantly improving the decision-making speed of the pilot.

[0036] Preferably in this embodiment, the light emitted by the light-emitting identifier 111 of the outermost height prediction layer 100 is green, indicating that the distance from the ground is sufficient and it is at a safe height; the height prediction layer 100 closer to the middle is yellow, reminding the pilot to enter the critical descent stage and pay close attention to the instruments and the external environment; the light emitted by the light-emitting identifier 111 of the innermost height prediction layer 100 is red, prompting the pilot that the ground is about to be touched. It goes without saying that the colors of the outermost height prediction layer 100, the height prediction layer 100 closer to the middle being yellow, and the innermost height prediction layer 100 can also be other colors, and this embodiment does not limit this.

[0037] Meanwhile, the colors of the light emitted by the light-emitting identifiers 111 on each height prediction layer 100 are different respectively. Combining with the different height identifiers on each height prediction layer 100, a dual coding of differentiated colors and height identifiers is set up. In complex weather conditions, it can significantly shorten the decision-making reaction time of the pilot and further increase the safety of the landing of the helicopter 200.

[0038] And / or, as Figure 3 and Figure 4 shown, the height marking further includes a pattern identifier 112. The pattern identifier 112 provides intuitive azimuth and landing point positioning guidance for the pilot of the helicopter 200. For example, the pattern identifier 112 set as an arrow indicates a safe path. The pattern identifier 112 and the light-emitting identifier 111 act together, which can not only adapt to long-distance recognition in a strong light environment (the outline of the pattern identifier 112 is clearly visible), but also avoid misjudgment caused by single-color reflection or background interference, enhancing the safety redundancy for landing in complex terrains.

[0039] As Figure 3 and Figure 4 shown, the pattern identifiers 112 of each height prediction layer 100 are all different. Each height prediction layer 100 adopts differentiated pattern identifiers 112, combined with color coding to form a multi-dimensional visual prompt system, which can strengthen hierarchical identification through pattern form differences in complex lighting or color vision limited scenarios, and reduce the landing risk through the "pattern-height" cognitive mapping, further increasing the safety of the landing of the helicopter 200.

[0040] A sand-proof layer is provided on the outer surface of the calibration plate 110. By setting the sand-proof layer, it can prevent the calibration plate 110 from being eroded by sand and dust, thereby increasing the service life of the calibration plate 110.

[0041] Preferably in this embodiment, the sand-proof layer can be a silica-based coating, polyurethane-aramid fiber, microporous metal filter screen, etc., which can be flexibly set according to the use requirements, and this embodiment does not limit this.

[0042] As Figure 4As shown, a sand guiding groove 113 is provided along the side length direction of the top surface of the calibration plate 110. The sand guiding groove 113 is used to collect the sand on the surface of the calibration plate 110. Before and after each helicopter lands 200 times, the ground crew blows the sand on the calibration plate 110 into the sand guiding groove 113 to ensure that the height markings on the calibration plate 110 are clear.

[0043] As Figure 4 and Figure 5 shown, a number of fasteners 114 are provided at the bottom of the calibration plate 110 for fixing the calibration plate 110 to the ground. In this embodiment, a sandy area is taken as an example. When installing the calibration plate 110, a number of fasteners 114 are pressed down to penetrate the sand layer, and the self-compaction of the sand is utilized to achieve stable ground gripping, so as to ensure the stable connection between the calibration plate 110 and the sandy area, and to prevent the calibration plate 110 from being lifted by the rotor airflow of the helicopter 200 and from being blown away by strong winds.

[0044] In this embodiment, the number of fasteners 114 can be 1, 2, 3 or more, and can be flexibly set according to the usage requirements. This embodiment does not limit this.

[0045] As Figure 5 shown, the fastener 114 has a soil-breaking part 1141. The soil-breaking part 1141 can quickly penetrate the sand layer and reduce the insertion resistance, thereby enabling the calibration plate 110 to be simply and quickly fixed to the sandy area.

[0046] Preferably in this embodiment, the soil-breaking part 1141 is a conical structure. Through the sharp end of the conical structure, the force is concentrated to quickly penetrate the sand layer and reduce the insertion resistance.

[0047] As Figure 5 shown, the top of the soil-breaking part 1141 has a groove 1142. After the fastener 114 is fixed to the sandy area, some soil and / or sand enter the groove 1142. The groove 1142 at the top of the soil-breaking part 1141 guides the natural filling of soil and / or sand during the anchoring process. Through the friction and negative pressure adsorption between the soil and / or sand, a self-locking effect is formed, so that the soil and / or sand are tightly fitted with the inner wall of the groove 1142, significantly improving the anchoring force.

[0048] Preferably in this embodiment, the soil-breaking part 1141 is formed by shelling to form the groove 1142 to increase the space of the groove 1142 and further improve the anchoring force.

[0049] Some embodiments of the present application also provide a method for assisting the landing of a helicopter 200 under sand-blind conditions, which is implemented based on the above-mentioned helicopter 200 sand-blind condition assisted landing system. The method includes the following steps: Step 100: Initially search for the takeoff and landing area 300 and initially determine the takeoff and landing area 300 as the landing point; Step 200: Identify the altitude markers on the outermost altitude prediction layer 100 in the current field of view, and determine the initial altitude of the current helicopter 200 from the ground based on the altitude markers; Step 300: During the continuous descent of the helicopter 200, identify the altitude markers on the altitude prediction layer 100 that first enter the field of view, and update the real-time altitude of the current helicopter 200 from the ground based on the altitude markers; Step 400: After identifying the innermost altitude prediction layer 100, the helicopter 200 approaches the ground and prepares to land.

[0050] It should be noted that in Steps 100 - 400, the pilot visually searches for the takeoff and landing area 300 and identifies the altitude markers on the altitude prediction layer 100.

[0051] It should also be noted that when multiple altitude prediction layers 100 enter the field of view simultaneously, update the real-time altitude of the current helicopter 200 from the ground based on the altitude markers of the altitude prediction layer 100 closer to the inside.

[0052] It should be noted that in this article, the terms "include", "comprise" or any other variant thereof are intended to cover non-exclusive inclusion, such that a process, method, article or device comprising a series of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article or device. Without further limitation, an element defined by the statement "comprising a..." does not exclude the presence of additional identical elements in the process, method, article or device comprising that element.

[0053] In addition, it should be pointed out that the scope of the methods and devices in the embodiments of the present application is not limited to performing functions in the order shown or discussed, and may also include performing functions in a substantially simultaneous manner or in the reverse order according to the functions involved. For example, the described methods may be performed in an order different from that described, and various steps may be added, omitted, or combined. Additionally, the features described with reference to certain examples may be combined in other examples.

[0054] The above is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of changes or substitutions, which should all be covered within the protection scope of the present invention.

Claims

1. An auxiliary landing system for a helicopter under sand-blind conditions, characterized in that, It includes multiple altitude prediction layers, which are used to predict the altitude from the ground during the helicopter landing process; The multiple altitude prediction layers are sequentially sleeved around the helicopter takeoff and landing area to form a warning area; Each altitude prediction layer has altitude markings. Along the direction from the outer edge to the center of the warning area, the altitude of the helicopter identified by the altitude markings gradually decreases.

2. The auxiliary landing system for a helicopter under sand-blind conditions according to claim 1, wherein, The radial dimension after the multiple altitude prediction layers are sleeved with each other is the same as the rotation area of the helicopter rotor; And / or, adjacent two altitude prediction layers are arranged at intervals; And / or, adjacent two altitude prediction layers are arranged closely; 3. The auxiliary landing system for a helicopter under sand-blind conditions according to claim 1, characterized in that The altitude prediction layer includes multiple calibration plates; The multiple calibration plates are arranged at intervals along the extension direction of the altitude prediction layer; The multiple calibration plates are respectively provided with the altitude markings, and the altitude of the helicopter identified by the altitude markings on the multiple calibration plates is the same.

4. The auxiliary landing system for a helicopter under sand-blind conditions according to claim 1, wherein The altitude marking includes a luminous identifier, and the luminous identifier is one or more of numbers, graphics, and symbols; And / or, the altitude marking includes a pattern identifier.

5. The auxiliary landing system for a helicopter under sand-blind conditions according to claim 3, wherein, The outer surface of the calibration plate is provided with a sand-proof layer.

6. The auxiliary landing system for a helicopter under sand-blind conditions according to claim 3, characterized in that, A sand guide groove is arranged along the side length direction of the top surface of the calibration plate, and the sand guide groove is used to collect the dust on the top surface of the calibration plate.

7. The auxiliary landing system for a helicopter under sand-blind conditions according to claim 3, characterized in that, Several fasteners are arranged at the bottom of the calibration plate for fixing the calibration plate to the ground.

8. The auxiliary landing system for a helicopter under sand-blind conditions according to claim 7, wherein, The bottom of the fastener has a soil-breaking part; A groove is arranged at the top of the soil-breaking part. After the fastener is fixed to the ground, part of the soil and / or sand enters the groove.

9. A method for assisted landing of a helicopter under sand-blind conditions, which is implemented based on the helicopter assisted landing system under sand-blind conditions according to any one of claims 1-8, characterized in that, The method includes the following steps: Preliminarily search for the takeoff and landing area and preliminarily determine the takeoff and landing area as the landing point; Identify the altitude markings on the outermost altitude prediction layer in the current field of view, and judge the initial altitude of the current helicopter from the ground based on the altitude markings; During the continuous descent of the helicopter, identify the altitude markings on the altitude prediction layer that first enters the field of view, and update the real-time altitude of the current helicopter from the ground based on the altitude markings; After identifying the innermost altitude prediction layer, the helicopter approaches the ground and prepares to land.

10. A method for assisting the landing of a helicopter under sand-blind conditions according to claim 9, characterized in that, When multiple altitude prediction layers enter the field of view at the same time, update the real-time altitude of the current helicopter from the ground based on the altitude markings of the altitude prediction layer closer to the inside.

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