Structural Design and Application of a Landing Assistance System for a Rotorcraft

Abstract

The present invention relates to the field and use of a landing assistance system for an aircraft with rotors. The present invention provides a design solution, method and application for an aircraft landing assistance system. The said solution and method mainly include a fixing device, a positioning mark, a hand-held attitude data alignment terminal for a rotorcraft, a platform stability attitude data acquisition and transmission system, and a light curtain forming device. After the landing assistance system is deployed, it can solve the problem of rotorcraft landing assistance under 9th-level heavy fog conditions at present; this product can also be applied to emergency rescue, emergency response to emergencies, emergency landing for field ground support, and aircraft landing assistance under low visibility conditions. The above-mentioned structural design solution and method of the aircraft landing assistance system are mainly applied to all aircraft platforms (including various surface ships and ground mobile platforms), including helicopters, such as helicopter transports, rotor unmanned fighter jets, rotor bombers, and including but not limited to aviation aircraft with rotor attitude adjustment, spacecraft, etc.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft landing assistance, and provides a structural design and application of an aircraft landing assistance system with a rotor, and particularly relates to a design of a light curtain forming device, a fixing device, a linkage design of an aircraft positioning aperture and a light curtain, and the reception, transmission, and use of attitude sensing data of an offshore platform, etc. Background Art

[0002] Existing rotor aircraft landing assistance products only provide landing assistance under high visibility conditions, require a large number of devices for fixed installation and operation, and in heavy fog conditions, the landing assistance system cannot accurately position and obtain the attitude data of the platform, and cannot land under the superposition conditions of severe sea conditions and low visibility conditions. Summary of the Invention

[0003] In view of this, the present invention provides a structural design and an application method of a landing assistance system for an aircraft with a rotor.

[0004] The technical solution adopted by the present invention is as follows:

[0005] A design of a light curtain system, and the center line area of the light curtain system is enhanced.

[0006] A design of a fixing device for quickly installing the light curtain forming device during emergency landing in the wild.

[0007] A linkage design of a positioning aperture and a light curtain for a rotorcraft.

[0008] A design for obtaining attitude sensing data of a non-fixed landing platform.

[0009] A receiving, transmitting, and applying method for attitude data of a non-fixed landing platform.

[0010] The beneficial effects of the present invention are as follows:

[0011] (1) Realize the use of the rotorcraft landing assistance system under heavy fog conditions.

[0012] (2) Can realize the precise landing of rotorcraft at a temporary landing site in the wild.

[0013] (3) Realize precise landing under low visibility conditions on a non-fixed platform.

[0014] (4) Realize the real-time transmission and application of attitude data of a non-fixed platform.

[0015] (5) Increase the takeoff and landing safety of all rotorcraft.

[0016] Description of the Drawings

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the accompanying drawings required for the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other accompanying drawings can be obtained based on these drawings.

[0018] Figure 1 It is a schematic diagram of the overall structure of the light curtain arrangement in the embodiment of the present invention;

[0019] Figure 2 It is a schematic diagram of the structure of the light curtain forming device in the embodiment of the present invention.

[0020] Figure 3 It is a schematic diagram of the structure of the fixing device in the embodiment of the present invention;

[0021] Figure 4 It is a schematic diagram of the installation structure of the fixing device, the attitude sensor and the transmitting device in the embodiment of the present invention.

[0022] Figure 5 It is a schematic diagram of the structure of the attitude data receiving device in the embodiment of the present invention.

[0023] Figure 6 It is a schematic diagram of the structure of quickly arranging the landing site in the embodiment of the present invention. Detailed implementation manners

[0024] The following will detail the present invention in conjunction with the accompanying drawings and specific embodiments. Here, the illustrative embodiments of the present invention and the description are used to explain the present invention, but not to limit the present invention.

[0025] The following combines the attached Figure 1 ~The attached Figure 6 Embodiments further describe the present invention in detail.

[0026] As Figure 1 shown, at the bottom of two mutually perpendicular light curtain planes, more than 1 rotary light curtain forming device ① is placed. The number of light curtain forming devices is from 1 to 999. The rotary light curtain forming device includes, but is not limited to, the fixed light curtain forming device formed by using the principle of the present invention, and a power supply is added.

[0027] As Figure 2 shown, on the light curtain forming device, a fog-penetrating lamp ① is added. The fog-penetrating lamp ① uses a fog-penetrating strong light lamp that can be purchased on the market, including, but not limited to, adding an automatic control program to it. The fog-penetrating lamp ① is installed in a rotating or permanently fixed manner.

[0028] As Figure 2As shown, on the light curtain forming device, there is a fixed bracket ② formed by using the principle of the present invention, which includes but is not limited to a grounding device, can be automatically leveled and fixed in the vertical direction.

[0029] As Figure 2 shown, on the light curtain forming device, including but not limited to, an electromagnetic strengthening device ③ is installed at the bottom of the fixed bracket ②, and the electromagnetic strengthening device ③ is combined with the electromagnetic plate device preset on the ground to form a stable ground platform.

[0030] As Figure 3 shown, for the fixing device, two wrench blocks ③ that can move left and right are connected by a spring member ①, and its locking member ② is connected to the ship platform or other platforms that need to monitor attitude data in real time.

[0031] As Figure 4 shown, attitude sensors and ranging sensors ① are arranged at any position of the fixing device, so that the attitude data and distance data of the platform where the fixing device is located are accurately transmitted to the sensors, and the number of sensors is from 1 to N.

[0032] As Figure 4 shown, sensor data transmitters ② are arranged at any position of the fixing device, so that the sensing data of the platform where the fixing device is located are accurately transmitted to the receiving device or platform of the rotary-wing aircraft, and the number of transmitters is from 1 to N.

[0033] As Figure 5 shown, on the platform of the aircraft with rotors, a Beidou communication terminal is used to receive short-distance attitude data. The receiving terminal includes but is not limited to receiving sensor data, distance, and altitude data, and the receiving method is wireless data reception, and the number of receivers is from 1 to N.

[0034] As Figure 6 shown, in actual application, the light curtain ③ formed by the light curtain forming device and the aircraft positioning auxiliary mark ② need to accurately locate the landing position ①, and together form a landing assistance system. After the positioning aperture formed by the aircraft positioning auxiliary mark ② is tangent to the light curtain ③ or the photoelectric positioning distance measurement reaches a certain distance, the landing position ① can be accurately judged.

[0035] After the attitude data of the landing platform is matched with the attitude data of the aircraft, accurate positioning can be achieved.

Claims

1. An aircraft landing assistance system with a rotor, characterized in that, It includes a fixing device and a light curtain forming device, which can form mutually perpendicular and adjacent light curtains at the accurate landing location of the rotorcraft; The fixing device is used to urgently fix the light curtain forming device on the ship deck or in the field area for precise assisted landing; The light curtain forming device includes a rotary or bracket type to form the light curtain necessary for the rotorcraft to land; The center line of the light curtain forming device has an obvious strong light feature, which is conducive to the accurate positioning of the rotorcraft; A color marking is applied at any position of the rotor of the rotorcraft to form a positioning aperture; after the formed positioning aperture is tangent to the light curtain, the landing position can be accurately judged.

2. The assisted landing system for an aircraft with rotors according to claim 1, characterized in that, The fixing device is equipped with an attitude sensor for measuring attitude data and a ranging sensor for measuring distance to monitor the attitude of the platform where the fixing device is located and the relative distance of the rotorcraft in real time.

3. The assisted landing system for an aircraft with rotors according to claim 2, characterized in that, The attitude data and distance data of the platform where the fixing device is located are wirelessly transmitted to the rotorcraft, and the rotorcraft can automatically perform real-time matching landing according to the attitude data.

4. The assisted landing system for an aircraft with rotors according to claim 3, characterized in that, It includes that the rotorcraft is equipped with a fixed or manually held sensor data receiver and transmits it to the control system, operation control system and operator of the rotorcraft.

5. The assisted landing system for an aircraft with rotors according to claim 4, characterized in that, It also includes a data receiving software system, which is applied to the assisted landing of all rotorcraft.

6. The assisted landing system for an aircraft with rotors according to claim 5, characterized in that, The rotorcraft assisted landing system is applied to the precise positioning and landing of the ship deck under low visual visibility conditions.

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