A helicopter assisted landing system and method under sand-blind conditions

Abstract

The present invention relates to the technical field of helicopter landing, and discloses a helicopter assisted landing system and method under sand-blind conditions. The system includes multiple altitude prediction layers; the multiple altitude prediction layers are sequentially nested around the helicopter take-off and landing area to form an early warning area; and each altitude prediction layer has an altitude marker. The method includes the following steps: preliminarily searching for the take-off and landing area, and preliminarily determining the take-off and landing area as the landing point; identifying the altitude marker on the outermost altitude prediction layer in the current field of view, and judging the initial altitude of the current helicopter from the ground based on the altitude marker; during the continuous descent of the helicopter, identifying the altitude marker on the altitude prediction layer that first enters the field of view, and updating the real-time altitude of the current helicopter from the ground based on the altitude marker; after identifying the innermost altitude prediction layer, the helicopter approaches the ground and prepares for landing. The present invention can solve the technical problem of the difficulty of helicopter landing under sand-blind conditions.

Description

Technical Field

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

[0002] As an important form of air transportation, helicopters have unique application value in complex terrain and adverse weather conditions. However, when landing on dusty terrain, helicopters often face the problem of wind-blown sand obstructing the pilot's vision, posing a serious threat to flight safety. Especially in dusty areas such as deserts and Gobi Desert, the airflow generated by the helicopter's rotors during landing can stir up large amounts of sand and dust, forming thick dust clouds that seriously affect the pilot's visual judgment and significantly increase the difficulty of landing.

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

[0004] The invention discloses an auxiliary landing system for a helicopter under sand-blind conditions, so as to solve the technical problem in the related art that it is difficult for a helicopter to land under sand-blind conditions.

[0005] In order to solve the above problems, the present invention adopts the following technical solutions:

[0006] In a first aspect, the present invention discloses a helicopter assisted landing system under sand-blind conditions, comprising a plurality of altitude prediction layers, the altitude prediction layers being used to predict the height of the helicopter from the ground during landing;

[0007] Multiple altitude prediction layers are sequentially connected around the helicopter take-off and landing area to form a warning area;

[0008] Each altitude prediction layer has an altitude mark. From the outer edge to the center of the warning area, the height of the helicopter marked by the altitude mark gradually decreases from the ground.

[0009] In a second aspect, the present invention discloses a method for assisting helicopter landing under sand-blind conditions, which is based on the helicopter assisting landing system under sand-blind conditions in the first aspect, and the method comprises the following steps:

[0010] Preliminarily search for the take-off and landing area and preliminarily determine the take-off and landing area as the landing point;

[0011] Identify the height markers on the outermost height prediction layer in the current field of view, and determine the initial height of the current helicopter from the ground based on the height markers;

[0012] During the continuous descent of the helicopter, the altitude marker on the altitude prediction layer that first enters the field of view is identified, and the real-time altitude of the current helicopter from the ground is updated based on the altitude marker;

[0013] After identifying the innermost altitude prediction layer, the helicopter approaches the ground and prepares to land.

[0014] The technical solution adopted by the present invention can achieve the following beneficial effects:

[0015] The helicopter assisted landing system under sand-blind conditions of the present application initially searches for a take-off and landing area in the air, preliminarily determines the take-off and landing area as a landing point, identifies the height mark on the outermost height prediction layer in the current field of view, and judges the initial height of the current helicopter from the ground based on the height mark; during the continuous descent of the helicopter, the height mark on the height prediction layer that first enters the field of view is identified, and the real-time height of the current helicopter from the ground is updated based on the height mark; after identifying the innermost height prediction layer, the helicopter approaches the ground and prepares to land. The present invention reduces the dimensionality of complex flight parameters into a graphical language that can be intuitively parsed by setting multiple height prediction layers of different sizes, establishes a strong mapping relationship between physical space and visual features, provides a clear visual reference for the pilot, helps him 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

[0016] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0017] Figure 1 2. It is a structural schematic diagram of the helicopter auxiliary landing system under sand-blind conditions of the present invention;

[0018] Figure 2 Schematic diagram of the helicopter of the present invention at different altitudes;

[0019] Figure 3 1. is a top view of the helicopter assisted landing system under sand-blind conditions of the present invention;

[0020] Figure 4 is an axonometric view of the calibration plate of the present invention;

[0021] Figure 5 yes Figure 4 Enlarged view of point A in the middle.

[0022] In the picture:

[0023] 100 - height prediction layer, 110 - calibration plate, 111 - luminous mark, 112 - pattern mark, 113 - sand guide groove, 114 - fastener, 1141 - soil breaking part, 1142 - groove;

[0024] 200 - helicopter;

[0025] 300-take-off and landing area. DETAILED DESCRIPTION

[0026] To make the objectives, technical solutions, and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail below. Obviously, the embodiments described are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other implementations obtained by those of ordinary skill in the art without inventive effort are within the scope of protection of the present invention.

[0027] The terms "first," "second," and the like in the specification and claims of this application are used to distinguish similar objects, and are not used to describe a specific order or precedence. It should be understood that the terms used in this manner are interchangeable where appropriate, so that the embodiments of this application can be implemented in an order other than that illustrated or described herein, and that the objects distinguished by "first," "second," and the like are generally of the same type, and do not limit the number of objects; for example, the first object can be one or more. In addition, the term "and / or" in the specification and claims refers to at least one of the connected objects, and the character " / " generally indicates that the objects connected are in an "or" relationship.

[0028] During actual operation, the inventors discovered that when the helicopter 200 lands on dusty ground, it often faces the problem of wind and sand blowing up and blocking the pilot's vision, which poses a serious threat to flight safety. Especially in areas with a lot of sand and dust, such as deserts and Gobi, the airflow generated by the rotors of the helicopter 200 during landing will stir up a large amount of sand and dust, forming a thick dust cloud, which seriously affects the pilot's visual judgment ability and makes landing significantly more difficult. Traditional landing assistance methods for helicopters 200 mainly include visual landmarks, navigation systems, and ground auxiliary facilities, but in strong wind and sand environments, these methods are often difficult to fully play their role. For example, visual landmarks are easily obscured by dust, making it difficult for pilots to accurately judge the distance between the helicopter 200 and the ground; although the navigation system can provide certain altitude data, it lacks intuitive visual references and is difficult to meet the pilot's operational needs in complex environments. In addition, existing ground auxiliary facilities are mostly designed for ordinary runways and are difficult to adapt to the special environment of dusty ground.

[0029] The following is combined with Figures 1 to 5, through specific embodiments and application scenarios, the helicopter assisted landing system and method under sand-blind conditions provided by this application are described in detail.

[0030] Some embodiments of the present application provide a helicopter 200 sand blind conditions assisted landing system, such as Figure 1-Figure 3 As shown, multiple height prediction layers 100 are included.

[0031] like Figure 1 and Figure 2 As shown, multiple altitude prediction layers 100 are sequentially nested around the take-off and landing area 300 of the helicopter 200 to form a warning area. The pilot determines the initial altitude by visually observing the maximum visible altitude prediction layer 100. As the smaller layers come into view, the altitude reference can be iteratively updated, such as Figure 2 Multiple altitude prediction layers 100 are sequentially nested around the take-off and landing area 300 of the helicopter 200, which can also ensure that the pilot can continuously observe the position changes of the calibration plate 110 during the landing process.

[0032] In this embodiment, the height prediction layer 100 may be circular, square, or other shapes, which is not limited in this embodiment.

[0033] like Figure 3 As shown, each altitude prediction layer 100 has an altitude marker. The altitude marker is used to predict the height of the helicopter 200 from the ground during landing. It reduces the complex flight parameters into an intuitive and analytic graphical language, establishes a strong mapping relationship between physical space and visual features, and provides a clear visual reference for the pilot to help him quickly determine the height and position of the helicopter 200, thereby effectively reducing the probability of touchdown accidents and significantly improving landing safety.

[0034] like Figure 1-Figure 3 As shown, the height of the helicopter 200, as indicated by the altitude markers, gradually decreases from the outer edge to the center of the warning area. Each altitude prediction layer 100 gradually decreases in height from the outer edge to the inner edge, reestablishing a spatial reference in extreme environments such as sand blindness, allowing pilots to land safely without relying too much on electronic equipment.

[0035] like Figure 1 and Figure 2 As shown, the radial size of the multiple altitude prediction layers 100 after being nested with each other is the same as the rotation area of the helicopter 200 rotor, so as to ensure that the pilot can continuously observe the position changes of the altitude prediction layers 100 during the landing process of the helicopter 200.

[0036] And / or, two adjacent height prediction layers 100 are arranged at intervals.

[0037] And / or, two adjacent height prediction layers 100 are set closely.

[0038] In some embodiments, any two adjacent altitude prediction layers 100 are spaced apart. Spaced apart, this can create a larger circle coverage area, optimizing spatial perception accuracy by expanding the gradient density of the visual scale. The spaced areas allow each layer of altitude markers to independently occupy a larger visual area, allowing pilots in higher airspace to detect warning signals from the outer altitude prediction layer 100 and adjust their course in advance.

[0039] In some embodiments, any two adjacent altitude prediction layers 100 are arranged in close proximity. This creates a visual contrast line between the two adjacent altitude prediction layers 100. During the descent of the helicopter 200, this visual contrast line serves as a warning to the pilot, prompting them to update their altitude reference. Furthermore, the visual contrast line allows the pilot to determine whether the helicopter 200 has drifted. If the helicopter 200 has drifted, the pilot will visually see a break or tilt in the visual contrast line, directly indicating the direction and magnitude of the drift, allowing the pilot to adjust the flight attitude of the helicopter 200.

[0040] In some embodiments, some adjacent height prediction layers 100 are spaced apart, while some adjacent height prediction layers 100 are placed close together. In this way, the spacing between adjacent height prediction layers 100 can be freely adjusted according to the terrain, which is suitable for laying in harsh environments such as deserts.

[0041] like Figure 3 As 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 extension direction of the height prediction layer 100. The height prediction layer 100 is formed by combining a plurality of calibration plates 110. During transportation, the plurality of calibration plates 110 can be stacked for transportation, saving space and making transportation more convenient. During installation, the plurality of calibration plates 110 can freely adjust the spacing and angles of the calibration plates 110 according to the undulations of the terrain, which is particularly suitable for the rapid construction of temporary landing and take-off sites in harsh environments such as deserts. During maintenance, any calibration plate 110 can be replaced independently when damaged, without the need for overall disassembly and assembly, thereby reducing maintenance costs.

[0042] Multiple calibration plates 110 are spaced apart. The space between any two adjacent calibration plates 110 serves as a dust accumulation buffer, preventing dust from accumulating excessively and covering the calibration plates 110. Furthermore, the space between the two adjacent calibration plates 110 serves as a passage for pilots entering or exiting helicopter 200, preventing them from stepping on calibration plates 110 and thus increasing their service life. Furthermore, the spacing between adjacent calibration plates 110 reduces the number of calibration plates 110 used, while ensuring that the altitude prediction layer 100 can be formed, thereby reducing costs.

[0043] As preferred in this embodiment, the spacing between any two adjacent height prediction layers 100 is 2m-5m. Of course, the spacing between any two adjacent height prediction layers 100 is not limited to 2m-5m, and can also be other lengths, which can be flexibly set according to design requirements and is not limited in this embodiment.

[0044] like Figure 3 and Figure 4 As shown, each altitude prediction layer 100 includes multiple calibration plates 110 with respective altitude markers. The altitude markers on these multiple calibration plates 110 indicate the same altitude above the ground for the helicopter 200. Multiple calibration plates 110 are independently marked with altitude markers, enhancing system reliability through segmented redundancy. Each calibration plate 110 functions as an independent information unit. Even if obscured by dust or partially damaged, the remaining calibration plates 110 can still be used to reconstruct a complete spatial reference grid. Furthermore, the modular design allows for dynamic adjustment of marker density based on the environment and reduces maintenance costs through partial replacement.

[0045] like Figure 3 and Figure 4 As shown, the height mark includes a light-emitting mark 111. The light-emitting mark 111 penetrates environmental interference through active light signals, significantly improving the reliability and real-time performance of the warning system.

[0046] As preferred in this embodiment, the luminous marker 111 is an LED lamp.

[0047] In this embodiment, the calibration board 110 is provided with a built-in battery to power the plurality of luminous markers 111. Furthermore, the built-in battery of the calibration board 110 can be charged by solar energy, wind-solar hybrid, or batteries based on the conditions of the site.

[0048] like Figure 3 and Figure 4 As shown, the luminous mark 111 is one or more of a number, a graphic, and a symbol. Specifically, there are multiple luminous marks 111, and the multiple luminous marks 111 form one or more of a number, a graphic, and a symbol.

[0049] As a preferred embodiment of this invention, the altitude markings are Arabic numerals formed by multiple luminous markings 111, thereby providing the pilot with the most intuitive altitude judgment of the altitude layer. For example, the altitude markings from the outermost layer to the innermost layer are 100, 80, 60, 40, and 20, respectively. Of course, the altitude markings can also be letters, Greek numerals, etc. formed by multiple luminous markings 111, and can be flexibly configured according to usage requirements, and this embodiment is not limited to this.

[0050] The luminous markers 111 on each altitude prediction layer 100 emit different colors of light. Through the color-differentiated altitude marker system, pilots can quickly establish the relationship between spatial position and operation phase during descent, significantly improving the pilot's decision-making speed.

[0051] As a preferred embodiment of this embodiment, the outermost altitude prediction layer 100 luminous marker 111 emits green light, indicating sufficient distance from the ground and a safe altitude. The middle altitude prediction layer 100 emits yellow light, reminding the pilot that they are entering the critical descent phase and need to pay close attention to the instrument and external environment. The innermost altitude prediction layer 100 luminous marker 111 emits red light, indicating that the pilot is about to touch down. Of course, the outermost altitude prediction layer 100, the middle altitude prediction layer 100, and the innermost altitude prediction layer 100 may also be other colors, and this embodiment is not limited to this.

[0052] At the same time, the color of light emitted by the luminous mark 111 on each altitude prediction layer 100 is different. Combined with the different altitude marks on each altitude prediction layer 100, dual coding of differentiated colors and altitude marks is set. In complex weather conditions, it can significantly shorten the pilot's decision-making reaction time and further increase the safety of the helicopter 200 landing.

[0053] and / or, such as Figure 3 and Figure 4 As shown, the altitude marking also includes a patterned mark 112. Patterned mark 112 provides helicopter 200 pilots with intuitive guidance for orientation and landing point location. For example, patterned mark 112, arranged in the form of an arrow, indicates a safe path. Patterned mark 112 works in conjunction with luminous mark 111, enabling long-range identification in bright lighting conditions (with the outline of patterned mark 112 clearly visible) while also preventing misidentification caused by single-color reflections or background interference, thereby enhancing safety redundancy for landings in complex terrain.

[0054] like Figure 3 and Figure 4 As shown, each altitude prediction layer 100 has a different pattern marker 112. Each altitude prediction layer 100 utilizes differentiated pattern markers 112, combined with color coding to form a multi-dimensional visual cue system. This system enhances layer recognition through pattern morphology differences in complex lighting or color-limited scenarios, reduces landing risk through "pattern-altitude" cognitive mapping, and further enhances the landing safety of the helicopter 200.

[0055] The outer surface of the calibration plate 110 is provided with a sandproof layer. The provision of the sandproof layer can prevent sand and dust from eroding the calibration plate 110, thereby increasing the service life of the calibration plate 110.

[0056] As preferred in this embodiment, the anti-sand layer can be a silica-based coating, polyurethane-aramid fiber, a microporous metal filter, etc., which can be flexibly set according to usage requirements, and this embodiment does not limit this.

[0057] like Figure 4 As shown, the top surface of the calibration plate 110 is provided with a sand guide groove 113 along its length. The sand guide groove 113 is used to collect sand on the surface of the calibration plate 110. Before and after each helicopter landing, the ground crew blows the sand on the calibration plate 110 into the sand guide groove 113 to ensure that the height markings on the calibration plate 110 are clear.

[0058] like Figure 4 and Figure 5 As shown, the bottom of calibration plate 110 is provided with a plurality of fasteners 114 for securing calibration plate 110 to the ground. This embodiment uses sand as an example. When installing calibration plate 110, the plurality of fasteners 114 press down and penetrate the sand layer, leveraging the density of the sand to achieve a secure grip. This ensures a stable connection between calibration plate 110 and the sand, preventing calibration plate 110 from being lifted by the rotor airflow of helicopter 200 or being blown away by strong winds.

[0059] In this embodiment, the number of fasteners 114 may be 1, 2, 3 or more, and may be flexibly arranged according to usage requirements, which is not limited in this embodiment.

[0060] like Figure 5 As shown, the fastener 114 has a soil-breaking portion 1141. The soil-breaking portion 1141 can quickly penetrate the sand layer and reduce insertion resistance, thereby allowing the calibration plate 110 to be simply and quickly fixed to the sand.

[0061] As preferred in this embodiment, the soil-breaking portion 1141 is a conical structure, which concentrates force through the sharp end of the conical structure, quickly penetrates the sand layer and reduces insertion resistance.

[0062] like Figure 5 As shown, the top of the soil-breaking portion 1141 has a groove 1142. After the fastener 114 is fixed to the sand, some soil and / or sand enters the groove 1142. During the anchoring process, the groove 1142 at the top of the soil-breaking portion 1141 guides the soil and / or sand to naturally fill in. The friction between the soil and / or sand and the negative pressure adsorption form a self-locking effect, so that the soil and / or sand are tightly embedded in the inner wall of the groove 1142, significantly improving the anchoring force.

[0063] As a preferred embodiment of the present invention, the ground-breaking portion 1141 is extracted to form a groove 1142 to increase the space of the groove 1142 and further enhance the anchoring force.

[0064] Some embodiments of the present application further provide a method for assisting landing of a helicopter under sand-blind conditions, which is implemented based on the above-mentioned helicopter assisting landing system under sand-blind conditions. The method includes the following steps:

[0065] Step 100: Preliminarily search for the take-off and landing area 300 and preliminarily determine the take-off and landing area 300 as the landing point;

[0066] Step 200: Identify the height mark on the outermost height prediction layer 100 in the current field of view, and determine the initial height of the current helicopter 200 from the ground based on the height mark;

[0067] Step 300: During the continuous descent of the helicopter 200, the altitude marker on the altitude prediction layer 100 that first enters the field of view is identified, and the real-time altitude of the current helicopter 200 from the ground is updated based on the altitude marker;

[0068] Step 400: After identifying the innermost altitude prediction layer 100, the helicopter 200 approaches the ground and prepares to land.

[0069] It should be noted that in steps 100 to 400 , the pilot visually searches for the take-off and landing area 300 and identifies the altitude mark on the altitude prediction layer 100 .

[0070] It should also be noted that when multiple altitude prediction layers 100 enter the field of view at the same time, the real-time altitude of the current helicopter 200 from the ground is updated based on the altitude mark of the altitude prediction layer 100 close to the inner side.

[0071] It should be noted that, in this document, the terms "comprises," "includes," or any other variations thereof are intended to encompass non-exclusive inclusion, such that a process, method, article, or apparatus comprising a series of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus. In the absence of further limitations, an element defined by the phrase "comprising a ..." does not exclude the presence of other identical elements in the process, method, article, or apparatus comprising the element.

[0072] Furthermore, it should be noted that the scope of the methods and apparatuses in the embodiments of the present application is not limited to performing functions in the order shown or discussed, but may also include performing functions substantially simultaneously or in reverse order depending on the functions involved. For example, the methods described may be performed in an order different from that described, and various steps may be added, omitted, or combined. Furthermore, features described with reference to certain examples may be combined in other examples.

[0073] The above description is only a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with this technical field can easily think of changes or replacements within the technical scope disclosed by the present invention, which should be covered by the scope of protection of the present invention.

Claims

1. A helicopter assisted landing system under sand blind conditions, characterized in that: It includes multiple altitude prediction layers, wherein the altitude prediction layers are used to predict the altitude of the helicopter from the ground during landing; The plurality of altitude prediction layers are sequentially nested around the helicopter take-off and landing area to form an early warning area; Each of the altitude prediction layers has an altitude mark, and the altitude of the helicopter from the ground marked by the altitude mark gradually decreases along the direction from the outer edge to the center of the warning area; The radial size of the plurality of height prediction layers after being nested with each other is the same as the rotation area of the helicopter rotor; two adjacent height prediction layers are arranged at intervals, or two adjacent height prediction layers are arranged closely; The altitude prediction layer includes a plurality of calibration plates; the plurality of calibration plates are arranged at intervals along the extension direction of the altitude prediction layer; the plurality of calibration plates are respectively provided with the altitude marks, and the heights of the helicopters indicated by the altitude marks on the plurality of calibration plates are the same from the ground; The helicopter assisted landing method under sand blind conditions includes the following steps: Preliminarily searching for a take-off and landing area, and preliminarily determining the take-off and landing area as a landing point; Identifying the height mark on the outermost height prediction layer in the current field of view, and determining the initial height of the current helicopter from the ground based on the height mark; During the continuous descent of the helicopter, the altitude marker on the altitude prediction layer that first enters the field of view is identified, and the real-time altitude of the current helicopter from the ground is updated based on the altitude marker; After identifying the innermost layer of the altitude prediction layer, the helicopter approaches the ground and prepares for landing; When multiple altitude prediction layers enter the field of view at the same time, the real-time altitude of the current helicopter from the ground is updated based on the altitude mark of the altitude prediction layer close to the inner side.

2. The helicopter assisted landing system under sand-blind conditions according to claim 1, characterized in that: The height mark includes a luminous mark, and the luminous mark is one or more of a number, a graphic, and a symbol; And / or, the height marking includes a tread pattern.

3. The helicopter assisted landing system under sand-blind conditions according to claim 1, characterized in that: The outer surface of the calibration plate is provided with a sand-proof layer.

4. The helicopter assisted landing system under sand-blind conditions according to claim 1, characterized in that: The top surface of the calibration plate is provided with a sand guide groove along the side length direction thereof, and the sand guide groove is used to collect sand and dust located on the top surface of the calibration plate.

5. The helicopter assisted landing system under sand-blind conditions according to claim 1, characterized in that: A plurality of fasteners are provided at the bottom of the calibration plate for fixing the calibration plate to the ground.

6. The helicopter assisted landing system under sand-blind conditions according to claim 5, characterized in that: The bottom of the fastener has a ground-breaking portion; The top of the soil-breaking portion is provided with a groove, and after the fastener is fixed to the ground, part of the soil and / or sand enters the groove.

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