Recovery docking device capable of being folded and unfolded

Abstract

The utility model belongs to the field of aircrafts, and particularly relates to a folding and unfolding recovery docking device. Comprising a linear module, a sliding block, a pull rod, a motor, a vertical rod, a connecting rod, a butt-joint rod, a base and a connecting seat; the recovery device has the repeated folding and unfolding capacity, the recovery device is folded, unfolded and folded along with the flight-docking-recovery state of the aircraft, the recovery device is folded in the aircraft in the flight stage and unfolded in the docking stage, the docking mechanism increases the recovery capacity of the storage device, the aerodynamic resistance of the aircraft is reduced, and the storage device is driven by a motor, so that the recovery efficiency is improved. The problem that a recovery device needs to be folded and unfolded in a reciprocating mode under the harsh constraint space condition is solved, and the modular design is adopted, so that the structure is ingenious, and driving is controllable.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft, specifically a compact, motor-driven, reciprocating folding and unfolding mechanism. It relates to a foldable and unfoldable recovery docking device. Background Technology

[0002] After completing its flight mission, a certain type of aircraft needs to be recovered and stored in a storage device. The storage device docks with the aircraft's recovery unit via a capture device. To avoid interference between the capture device and the aircraft during docking, the recovery unit typically protrudes from the aircraft's surface, resulting in an increased aircraft shape envelope and aerodynamic drag. The recovery process only occurs after the aircraft's flight mission is completed; the recovery unit is inactive during the flight phase, and the increased aerodynamic drag reduces the aircraft's range. Furthermore, the storage device has a limited size, and an increased aircraft shape envelope during recovery also reduces the storage device's recovery capacity. Utility Model Content

[0003] To effectively increase the recovery capacity of the storage device and reduce the aerodynamic drag of the aircraft, the outer envelope of the recovery aircraft needs to be minimized. Therefore, the recovery device must have the ability to repeatedly fold and unfold. The recovery device "folds-unfolds-folds" as the aircraft is in the "cruise-docking-recovery" state. During the flight phase, the recovery device is folded inside the aircraft, unfolded during the docking phase to facilitate docking with the capture device of the storage device, and folded again when returned to the storage device to increase the recovery capacity of the storage device. On the other hand, the aircraft system is complex, with a large number of accessories installed inside the fuselage and limited space. Therefore, the recovery device needs to be compact.

[0004] Utility Model Purpose

[0005] This invention addresses the aforementioned existing technology and recovery requirements by designing a foldable and deployable recovery docking device. The aim is to simplify and compact the mechanism design while reducing the aircraft's external envelope, thereby improving the recovery capability of the storage device and increasing the aircraft's range. Furthermore, the mechanism is motor-driven and can be repeatedly folded and unfolded, facilitating debugging.

[0006] Technical solution

[0007] A foldable and deployable recovery docking device includes a linear module 1, a slider 2, a pull rod 3, a motor 7, a vertical rod 5, a connecting rod 6, a docking rod 4, a base 8, and a connecting seat 9. The base 8 and the connecting seat 9 are fixed to the aircraft. One end of the connecting rod 6 is hinged to the connecting seat 9, and the other end of the connecting rod 6 is hinged to a first hinge point A on the docking rod 4. One end of the vertical rod 5 is hinged to the base 8, and the other end of the vertical rod 5 is hinged to a second hinge point B on the docking rod 4. The first hinge point A and the second hinge point B are on the same plane but different axes.

[0008] Slider 2 and upright 5 are connected by a hinge via pull rod 3. Linear module 1 converts the rotational drive of motor 7 into linear motion of slider 2. Slider 2, pull rod 3, upright 5, and base 8 constitute a crank-slider mechanism. The reciprocating linear motion of slider 2 drives the folding and unfolding of upright 5. Upright 5 and connecting rod 6 are hinged to connecting rod 7 via second hinge point B and first hinge point A, respectively. Upright 5, connecting rod 6, connecting rod 4, and aircraft fuselage constitute a four-bar linkage mechanism. Second hinge point B is the drive source for connecting rod 4, which enables the linkage between connecting rod 4 and upright 5.

[0009] When folding and unfolding, the docking rod 4 overlaps with the upright rod 5 to reduce the space occupied by the aircraft fuselage after folding. After recovery, the recovery docking device needs to be folded. At this time, the motor 7 acts in the reverse direction, the slider 2 slides forward, and the upright rod 5 changes from vertical to horizontal under the pull of the pull rod 3. At the same time, the upper hinge point of the upright rod 5 is driven by the upright rod 5, the connecting rod 6, the docking rod 4 and the connecting seat 9 to form a four-bar linkage mechanism. The docking rod 4 rotates 180° around the drive source and folds under the upright rod 5. The precise control of the slider 2 displacement is achieved by the motor 7 when the folding and unfolding are in place.

[0010] Furthermore, the mechanism can lock at any position during the folding to unfolding process.

[0011] Furthermore, the mechanism is fixed to the body via a base, enabling modular replacement.

[0012] Furthermore, the hinge axis of the connecting rod 6 and the aircraft fuselage is not on the same straight line as the rotation axis of the upright rod 5.

[0013] Furthermore, the head of the docking rod 4 is provided with a groove, which is used to connect and lock with the capture device during the docking process.

[0014] The beneficial effects of this application are as follows:

[0015] This invention designs a compact recovery docking mechanism that can be reciprocatedly folded and unfolded, which increases the recovery capacity of the storage device and reduces the aerodynamic drag of the aircraft. Driven by a motor, it solves the problem of the recovery device needing to be reciprocatedly folded and unfolded under harsh space constraints. This invention adopts a modular design, has a clever structure, and is controllable in drive. Attached Figure Description

[0016] Figure 1 Organizational layout diagram;

[0017] Figure 2 A schematic diagram showing the folding and unfolding of the recovery docking device;

[0018] Figure 3 This is a diagram showing the unfolded state;

[0019] Figure 4 This is a diagram showing the folded state;

[0020] The components are: 1. Linear module; 2. Slider; 3. Tie rod; 4. Connecting rod; 5. Vertical rod; 6. Connecting rod; 7. Motor; 8. Base; 9. Connecting seat. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions in the embodiments of this utility model will be described in more detail below with reference to the embodiments of this utility model. In the examples, the same or similar reference numerals denote the same or similar components or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this utility model. The embodiments described below with reference to the embodiments are exemplary and intended to explain this utility model, and should not be construed as limiting this utility model. All other embodiments obtained by those skilled in the art based on the embodiments of this utility model without creative effort are within the scope of protection of this utility model. The embodiments of this utility model will be described in detail below with reference to their specific implementation.

[0022] The structural layout of the recycling docking device is as follows: Figure 1 As shown, during deployment, the motor erects the upright via a linear module and a connecting rod. One end of the connecting rod is hinged to the aircraft fuselage, and the other end is hinged to the end of the docking rod. The hinge axis between the connecting rod and the aircraft fuselage is not on the same straight line as the upright's rotation axis. Due to geometric constraints, the connecting rod will pull up the docking rod during the upright's rotation. When the upright reaches the vertical position, the docking rod is parallel to or at a certain angle to the fuselage axis. After docking, the recovery docking device can be retracted back into the aircraft fuselage under the reverse action of the motor. The unfolded and folded states are as follows: Figure 2 As shown. This process utilizes the positive and negative action of an electric motor as a power source, and through a set of crank-slider mechanisms, enables the retraction docking device to repeatedly unfold and fold within a compact space.

[0023] like Figure 3 As shown, the utility model mainly consists of a linear module 1, a slider 2, a pull rod 3, a motor 7, a vertical rod 5, a connecting rod 6, a docking rod 4, a base 8, and a connecting seat 9. The base 8 and the connecting seat 9 are fixed to the aircraft. One end of the connecting rod 6 is hinged to the connecting seat 9, and the other end of the connecting rod 6 is hinged to the first hinge point A on the docking rod 4. One end of the vertical rod 5 is hinged to the base 8, and the other end of the vertical rod 5 is hinged to the second hinge point B on the docking rod 4. The first hinge point A and the second hinge point B are on the same plane but different axes.

[0024] Slider 2 and upright 5 are connected by a hinge via pull rod 3. Linear module 1 converts the rotational drive of motor 7 into linear motion of slider 2. Slider 2, pull rod 3, upright 5, and base 8 constitute a crank-slider mechanism. The reciprocating linear motion of slider 2 drives the folding and unfolding of upright 5. Upright 5 and connecting rod 6 are hinged to connecting rod 7 via second hinge point B and first hinge point A, respectively. Upright 5, connecting rod 6, connecting rod 4, and aircraft fuselage constitute a four-bar linkage mechanism. Second hinge point B is the drive source for connecting rod 4, which enables the linkage between connecting rod 4 and upright 5.

[0025] During folding and unfolding, the docking rod 4 overlaps with the upright rod 5 to reduce the space occupied by the aircraft fuselage after folding. After recovery, the recovery docking device needs to be folded. At this time, the motor 7 acts in reverse, the slider 2 slides forward, and the upright rod 5 changes from vertical to horizontal under the pull of the pull rod 3. At the same time, the upper hinge point of the upright rod 5 is driven by a four-bar linkage consisting of the upright rod 5, connecting rod 6, docking rod 4, and connecting seat 9. The docking rod 4 rotates 180° around the drive source and folds below the upright rod 5. The precise control of the slider 2's displacement is achieved by the motor when folding and unfolding are in place.

[0026] It will be understood by those skilled in the art that, unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. It should also be understood that terms such as those defined in general dictionaries should be understood to have the same meaning as in the context of the prior art, and should not be interpreted in an idealized or overly formal sense unless defined as herein. The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of this invention. It should be understood that the above descriptions are merely specific embodiments of this invention and are not intended to limit this invention. Within the spirit and principles of this invention, any person skilled in the art may modify or alter the disclosed technical content to create equivalent embodiments applicable to other fields. However, any simple modifications, equivalent changes, alterations, modifications, equivalent substitutions, improvements, etc., made to the above embodiments based on the technical essence of this invention without departing from the content of the technical solution of this invention should be included within the protection scope of this invention.

Claims

1. A foldable and deployable recycling docking device, characterized in that, It includes a linear module, a slider, a pull rod, a motor, a vertical rod, a connecting rod, a docking rod, a base, and a connecting seat; the base and the connecting seat are fixed to the aircraft, one end of the connecting rod is hinged to the connecting seat, and the other end of the connecting rod is hinged to the first hinge point A on the docking rod; one end of the vertical rod is hinged to the base, and the other end of the vertical rod is hinged to the second hinge point B on the docking rod, wherein the first hinge point A and the second hinge point B are on the same plane but on different axes; The slider and the upright are connected by a hinge via a pull rod. The linear module converts the rotational drive of the motor into the linear motion of the slider. The slider, pull rod, upright, and base constitute a crank-slider mechanism. The reciprocating linear motion of the slider drives the folding and unfolding of the upright. The upright and connecting rod are hinged to the connecting rod via the second hinge point B and the first hinge point A, respectively. The upright, connecting rod, connecting rod, and aircraft fuselage constitute a four-bar linkage mechanism. The second hinge point B is the drive source for the connecting rod, which enables the linkage between the connecting rod and the upright. When folding and unfolding, the docking rod overlaps with the upright to reduce the space occupied by the aircraft fuselage after folding. After recovery, the recovery docking device needs to be folded. At this time, the motor acts in reverse, the slider slides forward, and the upright changes from vertical to horizontal under the pull of the pull rod. At the same time, the upper hinge point of the upright drives a four-bar linkage consisting of the upright, connecting rod, docking rod and connecting seat. The docking rod rotates 180° around the drive source and folds under the upright. The precise control of the slider displacement is achieved by the motor when folding and unfolding are in place.

2. The apparatus as claimed in claim 1, characterized in that, It can lock at any position during the folding and unfolding process.

3. The apparatus as described in claim 1, characterized in that, Modular replacement is possible by connecting and fixing the base to the main body.

4. The apparatus as claimed in claim 1, characterized in that, The hinge axis of the connecting rod and the aircraft fuselage is not on the same straight line as the rotation axis of the upright.

5. The apparatus as claimed in claim 1, characterized in that, The head of the connecting rod is provided with a groove.

6. The apparatus as claimed in claim 5, characterized in that, The groove is used to connect and lock with the capture device during the docking process.

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