Special unpowered landing device for disc-shaped flying device

Abstract

The invention discloses an unpowered landing device special for a saucer-shaped aircraft, belongs to the technical field of saucer-shaped aircrafts, and aims to solve the problems that a traditional landing device is large in occupied space, complex to operate and free of autonomous speed and direction control. The device comprises an annular umbrella cloth storage container, cylindrical umbrella cloth, a rotatable ring, a hanging ring, a flexible hanging wire, a supporting pulley, a limiting device, an air leakage opening and an arc-shaped plate. The annular umbrella cloth storage container and the outer edge of the saucer-shaped aircraft are fixed or integrally designed, the upper edge of cylindrical umbrella cloth is bonded with a rotatable ring, the lower edge is bonded with the outer side of a hanging ring, and a flexible hanging wire is connected with the rotatable ring and the inner side of the hanging ring through a limiting device; the rotatable ring is supported by more than three supporting pulleys, is connected with an external power device through a clutch mechanism, and can drive the cylindrical umbrella cloth to be spirally stored; after the external power is cancelled, the gravity of the hanging ring drives the cylindrical umbrella cloth to unfold without jamming, and the opening and closing degree of the air outlet are adjusted in cooperation with the arc-shaped plate, so that the falling speed and the drifting direction are autonomously controlled. The device is high in adaptability, high in reliability and suitable for unpowered safe landing of the saucer-shaped aircraft in the vertical non-straight-through airflow state of the saucer body.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of saucer-shaped aircraft, and particularly discloses a special unpowered landing device for saucer-shaped aircraft, which is especially suitable for safe landing of saucer-shaped aircraft in an unpowered state under the condition of non-straight airflow on the saucer. BACKGROUND

[0002] At present, the safe landing of saucer-shaped aircraft is realized by the ways of ejecting a parachute, increasing functional wing pieces and embedding a floating airbag, but these landing devices have the problems of large space occupation, lack of self-direction deviation function or complex operation, especially the way of ejecting a parachute, which has large workload of opening, folding and retracting the parachute cloth, strict specification requirements, and may cause the parachute to fail to open due to carelessness. SUMMARY

[0003] In view of the above technical background, the present application proposes a special unpowered landing device for saucer-shaped aircraft, which is in the form of a parachute together with the saucer-shaped aircraft, and the specific content is as follows. The special unpowered landing device for saucer-shaped aircraft comprises a core structure including a ring-shaped parachute storage container, a cylindrical parachute, a rotatable ring, a hanging ring, a hanging line, a supporting pulley and a limiting device, a gas vent and a circular arc-shaped plate corresponding to the gas vent.

[0004] The ring-shaped parachute storage container is fixedly connected to the outer edge of the saucer-shaped aircraft or is designed and manufactured together with the saucer-shaped aircraft.

[0005] The upper edge of the cylindrical parachute is adhesively fixed to the rotatable ring, and the lower edge is adhesively fixed to the outer side of the hanging ring.

[0006] The hanging line is in the form of a ring array and has multiple roots, one end of each hanging line is fixed to the rotatable ring, the other end is fixed to the inner side of the hanging ring after passing through the limiting device.

[0007] The rotatable ring is supported and rotated by three or more supporting pulleys arranged in a ring array, and the rotatable ring and the external power acting device are connected in a clutching manner and are controlled by an electromagnetic control device or a mechanical control device.

[0008] The limiting device is mainly used for flexibly controlling the upward and downward movement of the hanging ring; when the rotatable ring rotates in a certain direction under the action of external power, the cylindrical parachute is automatically stored into the ring-shaped parachute storage container in a spiral manner until the hanging ring reaches the opening of the ring-shaped parachute storage container, that is, the hanging ring is also or equivalent to the ring-shaped cover plate at the bottom of the ring-shaped parachute storage container; when the external power acting on the rotatable ring is removed, the cylindrical parachute is rapidly unfolded under the action of gravity of the hanging ring without being blocked, and then forms a parachute-like shape together with the saucer-shaped aircraft, thereby slowing down the falling speed of the saucer-shaped aircraft.

[0009] Further, to control the downward landing speed and directional deviation of the saucer-shaped aircraft and achieve safe landing at a fixed point, a plurality of openable and closable air vents are arranged in a ring array on the combination part of the saucer-shaped aircraft and the ring-shaped umbrella cloth storage container and the outer side of the ring-shaped umbrella cloth storage container, preferably the openable and closable air vents are designed on the front, rear, left and right positions, and the opening and closing degree of the air vents is adjusted by rotating and moving up and down or left and right on the circular arc-shaped plate corresponding to the air vents, so as to independently control the falling speed and drifting direction of the saucer-shaped aircraft.

[0010] In summary, the present application aims at the core pain points of the traditional saucer-shaped aircraft without power landing device, such as large space occupation, complex operation and lack of autonomous control ability, and provides a set of power-free landing solution with strong adaptability, high reliability and controllability through innovative structure design and function optimization. The integrity and innovation of the technical scheme can be comprehensively described from the following three aspects.

[0011] 1. Integrated structure design: optimize space utilization and simplify body layout: the device takes the "ring-shaped umbrella cloth storage container" as the core bearing component, which is fixedly connected or integrally designed with the outer edge of the saucer-shaped aircraft, without the need for additional independent umbrella compartment or wing installation space, perfectly adapting to the streamlined body structure of the saucer-shaped aircraft, and fundamentally solving the problem of "large space occupation" of the traditional pop-up landing umbrella and functional wing. At the same time, the connection logic between the core components is highly integrated: the upper and lower edges of the cylindrical umbrella cloth are respectively bonded and fixed with the rotatable ring and the hanging ring, and the hanging lines are arranged in a ring array and connected with the two through the limiting device, which not only ensures the structural stability, but also avoids component redundancy; especially the "hanging ring" is designed as the "ring-shaped umbrella cloth storage container bottom ring-shaped cover plate" or equivalent structure, and the hanging ring can directly block the container port when stored, without the need for additional design of cover plate components, further simplifying the structure, reducing the storage volume and improving the space utilization rate.

[0012] 2. Innovative Operational Logic: Compared to the strict specifications for folding and unfolding the canopy of traditional parachutes, the core operation (folding / unfolding) of this device is simpler and more reliable. The rotatable ring and the external power unit are connected via a "clutch mechanism," with power switching achieved through electromagnetic or mechanical control. When folding is required, the clutch engages, and the external power drives the rotatable ring to rotate, causing the cylindrical canopy to spirally fold into the container until the lifting ring (cover) seals the container opening. The entire process requires no complex manual intervention. When the external power is deactivated, the clutch disengages, and the cylindrical canopy unfolds quickly using only the weight of the lifting ring itself, eliminating the need for complex mechanical triggering mechanisms and avoiding the risk of "opening failure" common in traditional parachutes. The limiting device uses a "flexible control" method, ensuring that the lifting ring moves only in the vertical direction, preventing the canopy from becoming entangled or shifted during unfolding / folding, while also buffering the impact force when the lifting ring falls, improving structural lifespan and unfolding stability.

[0013] 3. Functional expansion and upgrade: This invention breaks through the limitations of traditional devices that "can only passively decelerate and have no autonomous adjustment capability", and achieves dual autonomous and precise control of "speed + direction" in the case of unpowered descent through two major functional designs. The annular parachute storage container features four vents that can be opened and closed: front, back, left, and right. This allows for adjustment of airflow distribution not only through the "opening / closing state" but also through control of airflow loss through the "degree of opening / closing." For example, increasing the vent opening degree reduces air pressure below the parachute, weakening the deceleration effect and increasing descent speed; decreasing the opening degree increases air pressure, enhancing the deceleration effect and slowing descent speed, thus achieving flexible adjustment of landing speed. Secondly, by differentially controlling the opening and closing states of the four vents, the aircraft can be offset using the difference in airflow forces. For instance, when offsetting to the right, opening the right vent (or increasing the right vent opening degree) results in greater airflow loss on the right than on the left, strengthening the upward force of the airflow on the parachute on the left, thereby causing the aircraft to adjust to the right and precisely achieve a "safe landing at a designated point," adapting to complex scenarios such as narrow spaces and designated landing points.

[0014] In summary, this invention comprehensively solves the core defects of traditional unpowered landing devices through triple innovations of integrated structure, simplified operation, and controllable function. It provides a better technical solution for the safe landing of disc-shaped aircraft in unpowered scenarios, and has the advantages of technological innovation, engineering practicality, and patent protection, with broad application prospects. Attached Figure Description

[0015] Figure 1 is a simplified structural diagram of a non-powered landing device for a disc-shaped flying vehicle according to the present invention.

[0016] Figure 2 is an enlarged view of the component inside the circle in Figure 1.

[0017] In the figure: 1. saucer-shaped aircraft; 2. annular umbrella cloth storage container; 3. cylindrical umbrella cloth; 4. C-shaped rotatable ring; 5. bottom cover plate type inverted π-shaped hanging ring; 6. flexible hanging line; 7. supporting pulley; 8. limiting device; 9. air vent; 10. circular arc plate. DETAILED DESCRIPTION

[0018] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only one of the embodiments of the present application, not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0019] Embodiment 1: Referring to FIG. 1, a saucer-shaped aircraft special-purpose unpowered landing device, the core structure includes an annular umbrella cloth storage container 2, a cylindrical umbrella cloth 3, a C-shaped rotatable ring 4, a bottom cover plate type inverted π-shaped hanging ring 5, a flexible hanging line 6, a supporting pulley 7, a limiting device 8, an air vent 9, and a circular arc plate 10 corresponding to the air vent, etc.

[0020] The annular umbrella cloth storage container 2 is fixedly connected with the outer edge of the saucer-shaped aircraft 1, or is designed and manufactured integrally with the saucer-shaped aircraft.

[0021] The upper edge of the cylindrical umbrella cloth 3 is adhesively fixed with the inner side of the C-shaped rotatable ring 4, and the lower edge is adhesively fixed with the outer side stem ring of the bottom cover plate type inverted π-shaped hanging ring 5.

[0022] The hanging line 6 is in the form of multiple rings arranged in an annular array, one end of each hanging line is fixed with the C-shaped rotatable ring 4, after passing through the limiting device 8, the other end is fixed with the inner side stem ring of the bottom cover plate type inverted π-shaped hanging ring 5.

[0023] The C-shaped rotatable ring 4 is internally supported for rotation by three or more supporting pulleys 7 arranged in an annular array, and the rotatable ring and the external power acting device are preferably in a clutching mode, controlled by an electromagnetic or mechanical control device.

[0024] The main function of the limiting device 8 is to flexibly control the up-and-down movement of the bottom cover plate type inverted π-shaped hanging ring 5; when the C-shaped rotatable ring 4 rotates in a certain direction under the action of external power, the cylindrical umbrella cloth 3 is automatically and spirally stored into the annular umbrella cloth storage container 2, until the bottom cover plate type inverted π-shaped hanging ring 5 reaches the mouth of the annular umbrella cloth storage container; when the external power acting on the rotatable ring is removed, under the action of the gravity of the bottom cover plate type inverted π-shaped hanging ring 5, the cylindrical umbrella cloth 3 rapidly expands without any blockage when the bottom cover plate type inverted π-shaped hanging ring falls, and then forms a shape similar to a parachute together with the saucer-shaped aircraft 1, thereby slowing down the falling speed of the saucer-shaped aircraft.

[0025] Further, to control the downward landing speed and directional deviation of the saucer-shaped aircraft 1 and achieve safe landing at a fixed point, a closable air release port 9 is designed at the front, back, left and right of the combination part of the saucer-shaped aircraft and the annular umbrella cloth storage container 2 and the outer side surface of the annular umbrella cloth storage container. By controlling the up and down or left and right movement of the circular arc plate 10 at the air release port, the opening and closing degree of the air release port is adjusted to achieve autonomous control of the downward landing speed and drift direction of the saucer-shaped aircraft.

[0026] In summary, the embodiment designs the structure, connection mode and control logic of the core components to convert the technical solution of the invention from "theoretical concept" to "machinable, assemblable and operable" entity solution. Not only does it verify the feasibility of the previous innovative design, but also further strengthens the reliability and practicality of the device through detail optimization, which can be expanded in three aspects.

[0027] 1. Precise design of component shape and connection to ensure stable structure and functional landing: The embodiment optimizes the shape and connection relationship of the key components to provide a foundation for stable operation of the device. The shape of the C-shaped rotatable ring is selected: Compared with the ordinary ring structure, the C-shaped opening design is convenient for the connection of the clutch mechanism of the external power device (such as gear meshing, belt transmission, etc.), and can reduce the processing difficulty and weight without affecting the stability of rotation, which meets the lightweight demand of the saucer-shaped aircraft. At the same time, it is limited that "the inside is supported by three or more ring arrays of supporting pulleys", which can evenly distribute the force when the rotatable ring rotates, avoid eccentricity and jamming, and ensure the smoothness of the cylindrical umbrella cloth storage / expansion. The differential connection function of the inner and outer stem rings of the hanging ring is clearly defined - the outer stem ring is bonded to the lower edge of the cylindrical umbrella cloth, and the inner stem ring is fixed to the flexible hanging line. This double-stem ring structure not only realizes the core function of "hanging ring serving as a container bottom cover" (sealing the container opening when storing), but also avoids interference between the umbrella cloth and the hanging line during movement through the division of labor between the inner and outer stem rings, solving the coordination problem that may be caused by "single structure with multiple functions". At the same time, the selection of "flexible hanging line" and the "flexible control" of the limiting device further buffer the impact force when the hanging ring falls, avoiding component damage caused by rigid connection.

[0028] 2. The concretization of control logic reduces operational complexity and failure risk. The embodiment transforms the "abstract control method" mentioned above into a "concrete operation path", which greatly improves the operability and reliability of the device. The rotatable ring and the external power unit are connected by an electromagnetic or mechanical control device, without specifying specific control parameters (such as electromagnetic attraction or mechanical transmission ratio). This maintains the flexibility of the technical solution while ensuring the use of mature control technology to avoid malfunctions caused by complex control logic. When driven by external power, the rotatable ring drives the cylindrical parachute fabric to "spiral retraction" until the hanging ring seals the container opening. The entire process requires no manual intervention, solving the operational pain point of "manual folding and retraction" in traditional parachutes. A new "arc plate 10" is added as a control component for the vent. The opening and closing degree of the vent are adjusted by "moving the arc plate up and down or left and right." For example, when it is necessary to reduce the descent speed, the arc plate of the right vent is moved to the left to reduce the vent opening, reduce airflow loss, and enhance the deceleration effect of the parachute fabric. When it is necessary to shift to the left, the arc plate of the left vent is moved upward to increase the opening of the left vent, using the pressure difference of the airflow on the left and right to adjust the fuselage. This mechanical control method does not rely on complex sensing and electronic control systems, has a fast response speed and low failure rate, and is especially suitable for stable control requirements in the absence of power.

[0029] 3. Enhanced Scene Adaptability, Expanding the Device's Practical Value: Through detailed design, the embodiment makes the device more adaptable to the actual application scenarios of the disc-shaped aircraft. It emphasizes "no jamming" during the deployment of the cylindrical parachute, addressing the pain point of traditional parachutes where "parachute fabric entanglement leads to deployment failure." Through the smooth rotation of the C-shaped rotating ring, the circular array distribution of flexible suspension lines, and the reasonable division of labor among the two stem rings, the structure ensures no entanglement or deviation during parachute deployment, making it particularly suitable for the "time-sensitive requirements" of unpowered emergency landings (requiring rapid deployment and deceleration). The four-way vents, combined with the adjustment of the arc-shaped plate, achieve both "controllable descent speed" (opening adjustment) and "controllable drift direction" (differentiated opening and closing), adapting to various complex scenarios—such as landing in narrow urban areas, where speed can be controlled by fine-tuning the vent opening to avoid excessively rapid impact with the ground; and when the designated landing point deviates, the direction can be adjusted by opening and closing a single vent, without relying on external auxiliary equipment, truly achieving "autonomous and precise landing in an unpowered state."

[0030] In summary, the embodiment presents a "landing plan" of the special unpowered landing device for disc-shaped aircraft by accurately selecting the shape of components, reasonably designing the connection relationship, and visualizing the control logic. The design not only follows the core innovation of "structural integration, simplified operation, and controllable function" mentioned above, but also solves the problems of synergy and reliability that may be faced when transforming the "theoretical plan" into an actual product through detail optimization. At the same time, it does not add excessive specific parameter limitations, balances the engineering practicability and patent protection range, lays a solid foundation for subsequent processing, testing, and promotion of the device, and has a high technical transformation value and market application prospect.

Claims

1. A disc-shaped aircraft specific unpowered landing device, characterized in that, The umbrella includes a ring-shaped umbrella cloth storage container (2), a cylindrical umbrella cloth (3), a rotatable ring (4), a hanging ring (5), a plurality of flexible hanging lines (6), at least three supporting pulleys (7), a limiting device (8), at least two air vents (9), and a circular arc plate (10) corresponding to each air vent (9). The ring-shaped umbrella cloth storage container (2) is used for accommodating the cylindrical umbrella cloth (3), and the shape of the ring-shaped umbrella cloth storage container (2) is arbitrary, which is fixedly connected with the outer edge of the disc-shaped aircraft (1), or the ring-shaped umbrella cloth storage container (2) is designed in an integrated manner with the disc-shaped aircraft (1). The upper edge of the cylindrical umbrella cloth (3) is fixedly connected with the rotatable ring (4), and the lower edge of the cylindrical umbrella cloth (3) is fixedly connected with the outer side of the hanging ring (5). The plurality of flexible hanging lines (6) are arrayed in a ring-shaped direction, one end of each of the flexible hanging lines (6) is fixed with the rotatable ring (4), and the other end of each of the flexible hanging lines (6) is fixed with the inner side of the hanging ring (5) after passing through the limiting device (8), and the limiting device (8) is used for flexibly restricting the hanging ring (5) to move up and down in a vertical direction. The at least three supporting pulleys (7) are arrayed in a circumferential direction of the rotatable ring (4), and the supporting pulleys (7) are used for supporting the rotatable ring (4) and enabling the rotatable ring (4) to rotate around a central axis thereof; the rotatable ring (4) is connected with an external power acting device through a clutch mechanism, the clutch mechanism is controlled to be turned on or turned off by an electromagnetic control device or a mechanical control device, so as to drive the rotatable ring (4) to drive the cylindrical umbrella cloth (3) to be spirally accommodated into the ring-shaped umbrella cloth storage container (2), or when the clutch mechanism is disconnected, the cylindrical umbrella cloth (3) is unfolded without being blocked under the action of gravity of the hanging ring (5), and the unfolded cylindrical umbrella cloth (3) cooperates with the disc-shaped aircraft (1) to form a parachute-like structure. The at least two air vents (9) are arranged on the outer side of the ring-shaped umbrella cloth storage container (2), and the circular arc plate (10) is movably arranged at the air vent (9), the opening and closing state and the opening and closing degree of the air vent (9) are controlled by adjusting the moving distance of the circular arc plate (10), so as to realize the autonomous control of the landing speed and the drifting direction of the disc-shaped aircraft (1).

2. The disc-shaped aircraft-specific unpowered landing device of claim 1, wherein, The fixing connection mode of the cylindrical umbrella cloth (3) and the rotatable ring (4) is adhesion, and the fixing connection mode of the cylindrical umbrella cloth (3) and the outer side of the hanging ring (5) is adhesion.

3. The disc-shaped aircraft-specific unpowered landing device of claim 1, wherein, The number of the supporting pulleys (7) is three or more, and the supporting pulleys (7) are uniformly and interval distributed in the circumferential direction of the rotatable ring (4).

4. The disc-shaped aircraft-specific unpowered landing device of claim 1, wherein, The number of the air vents (9) is preferably four, and the four air vents (9) are respectively arranged at the front end, the rear end, the left end and the right end of the outer side of the ring-shaped umbrella cloth storage container (2).

5. The disc-shaped aircraft-specific unpowered landing device of claim 4, wherein, The moving direction of the circular arc plate (10) is upward and downward movement or left and right rotation movement, and the movement of the circular arc plate (10) is controlled by an electromagnetic driving assembly or a mechanical driving assembly.

6. The disc-shaped aircraft-specific unpowered landing device of claim 1, wherein, The hanging ring (5) is preferably a bottom cover plate type inverted π-shaped hanging ring, the diameters of the inner and outer stem rings of which are adapted to the opening of the annular umbrella cloth storage container (2) for plugging the opening of the annular umbrella cloth storage container (2) when the cylindrical umbrella cloth (3) is stored.

7. The disc-shaped aircraft-specific unpowered landing device of claim 1, wherein, The rotatable ring (4) is preferably a C-shaped or circular tube-shaped rotatable ring for adapting the connection of the external power acting device and the clutch mechanism.

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