Spaceflight variant aircraft deformation structure system

Abstract

The invention provides a space variant aircraft deformation structure system which is composed of a translation hinge structure, a rotation hinge structure, a translation servo motor, a telescopic wing, a folding wing and an installation support subsystem. The translation hinge structure and the rotation hinge structure with multi-scale gaps are designed based on the modularization concept; by replacing translational hinge and rotary hinge structures with different gap scales, the reliability of deformation motion of a deformation structure system is improved, and the method is also suitable for research on dynamic characteristics of a nonlinear multi-body system with a gap deformation structure.

Description

Technical Field

[0001] The present invention belongs to the technical field of deformable structure systems, and in particular relates to a deformable structure system for a spacecraft. Background Art

[0002] With the rapid development of the defense and military industries, highly maneuverable and long-duration cross-domain flight capabilities are key development directions for spacecraft to enhance their single-service performance. These vehicles operate over a wider speed range and larger airspace. Traditional fixed-geometry aerospace vehicles struggle to balance lift-to-drag performance requirements across various speed and airspace ranges, significantly constraining their overall performance. To adapt to complex and diverse mission environments encompassing a wide speed range and large airspace, morphing vehicles have become a research hotspot and a key development direction driven by mission requirements. Compared to fixed-geometry vehicles, morphing vehicles can adapt their wing shape and span to different speed and airspace ranges, resulting in improved aerodynamic characteristics. This improves flight efficiency and maneuverability in diverse flight environments, representing a key technological approach to supporting cross-domain flight and efficient free flight. Morphing vehicles are generally foldable rudder vehicles. Due to changes in mission profiles, flight environments, and structures, future spacecraft will differ significantly from traditional ones in terms of payload environments, structural dynamics, and other aspects, presenting numerous technical challenges. The deformable structure of a morphing vehicle is the component that enables the morphing vehicle to "morph." The nonlinear multi-body system dynamics of the deformable structure, especially the mechanism motion characteristics, are important parameters in the design of aerospace morphing vehicles. They are directly related to the reliability of the morphing configuration of the morphing vehicle, and thus affect the flight stability of the morphing vehicle across speed and airspace domains. The following key technologies need to be focused on for aerospace deformable structure systems:

[0003] ① Gap scale design of deformable structural system

[0004] The deformable structure of a spacecraft typically consists of retractable wings, folding wings, a guide motion assembly, and a locking mechanism. To achieve high aerodynamic efficiency, the deformation of a morphing vehicle should be continuous and smooth, resulting in gaps in the guide assembly. During the deformation process, these gaps cause mechanical phenomena such as contact deformation, adhesion, and frictional sliding between the guide assembly structures. This can lead to jamming of the guide assembly, posing significant challenges to the design of the deformable structure system and the reliability assessment of the mechanism. Furthermore, compared to other morphing vehicles, the deformation cycle of a spacecraft is short (deployment time is between 2-4 seconds), resulting in typical sudden changes in the aerodynamic characteristics of the deformable structure. The sudden external loads borne by the entire deformable structure exacerbate the "random" nature of the gap effect, further increasing the difficulty of evaluating the reliability of the deformable structure mechanism. Therefore, the gap design of the deformable structure system has a significant impact on the performance of the deformable structure mechanism.

[0005] ② Design of translational hinge and rotational hinge structures of deformation structure system

[0006] The deformable structure of a spacecraft is mainly used to realize the functions of telescopic wings extension and retraction, and folding wings deployment / recovery. At the same time, considering the special use requirements and operating environment of the deformable structure of a spacecraft, the overall deformable structure system must meet certain load-bearing requirements. As the main components for realizing deformation movement, the structural design of the translational hinge and rotational hinge structures has a very important impact on the performance of the mechanism. Traditional translational hinge and rotational hinge structures are generally mainly used to realize movement functions, and the external loads they bear are small, which cannot meet the application requirements of spacecraft. Therefore, designing translational hinge and rotational hinge structures with movement and load-bearing capabilities is one of the key issues that need to be solved urgently.

[0007] ③Deformation structure dynamic system design

[0008] The power system for a morphing structure of a spacecraft primarily consists of four components: a translational servo motor, a transmission mechanism, a power source, and a servo control system. Depending on the layout of the translational servo motors used to achieve the morphing motion, there are two main approaches to the design of the morphing structure's power system: 1) Using a single translational servo motor—driven by a single translational servo motor through a transmission design—to achieve the telescopic wing extension and folding wing deployment. This approach offers advantages in terms of a simple servo control system and good motion control coordination. However, its disadvantages include a complex transmission mechanism, which can easily cause component jamming. Furthermore, the large number of moving parts in the transmission mechanism complicates the analysis of the nonlinear multi-body dynamic characteristics of the mechanism. 2) Using two translational servo motors—one for telescopic wing extension and the other for folding wing deployment. This approach offers advantages in terms of simple transmission mechanism design, high reliability, and reduced complexity in analyzing the nonlinear multi-body dynamic characteristics of the mechanism. However, its disadvantage is the increased difficulty in controlling the servo control system coordination. Overall, the power system design is based on the actual engineering requirements of the morphing structure of a spacecraft. Summary of the Invention

[0009] This paper, based on the unique operational requirements and operating environment of spacecraft, provides a deformable structure system for spacecraft. Based on a modular design concept, translational and rotational articulated structures with multi-scale gaps are designed. By replacing translational and rotational articulated structures with different gap scales, the system not only improves the reliability of deformation motion and effectively avoids sticking, but also is suitable for studying the dynamic characteristics of nonlinear multi-body systems with gap-deforming structures.

[0010] The present invention provides a deformable structure system for a spacecraft. The deformable structure comprises two sets of translational articulated structures, one set of rotational articulated structures, two sets of translational servo motors, a pair of telescopic wings, a pair of folding wings, and a set of mounting brackets. The translational and rotational articulated structures are manufactured from steel to ensure proper component wear during movement. The telescopic wing skin is made of high-temperature resistant materials, and the internal frame structure is 3D-printed from aluminum alloy. The skin and frame structure are assembled using adhesive bonding and rivets. The folding wing skin is also manufactured from high-temperature resistant materials, and the internal frame beam structure is made from aluminum alloy. The skin and frame beam structure are processed using an embedded integrated molding process. The mounting bracket is made of aluminum alloy.

[0011] The translational articulated structure in the deformation structure system of the aerospace variant aircraft of the present invention includes a slider and a guide rail, wherein the gap between the slider and the guide rail is designed based on the proposed gap scale formula, and the slider finally realizes multi-scale gap matching; the rotational articulated structure includes a rotating shaft and a base, wherein the gap between the rotating shaft and the base is also designed based on the proposed gap scale formula, and the rotating shaft finally realizes multi-scale gap matching; the telescopic wing includes a skin and a frame structure, and the frame structure is used to carry and place two sets of translational servo motors; the folding wing includes a skin and a frame beam structure, and the frame beam structure is used to carry; the power system is mainly composed of a translational servo motor, a transmission mechanism, a power source, and a servo control system, wherein the power source and the servo control system are installed in the cabin of the variant aircraft, and will not be described in detail here. The mounting bracket is used to install the internal frame structure and guide rails of the telescopic wing and to push the translational servo motor of the telescopic wing, and the mounting bracket is connected to the fuselage of the aerospace variant aircraft.

[0012] The deformable structural system of this invention features continuous and smooth deformation, modular motion components, and strong control coordination. It effectively supports the design and application of deformable structural systems for aerospace vehicles. It also has practical engineering significance for advancing the research on the dynamic characteristics of nonlinear multi-body systems with gap structures and the optimization of control design for deformable structural systems.

[0013] The present invention designs translational hinge and rotational hinge structures with multi-scale gaps based on a modular concept. By replacing translational hinge and rotational hinge structures with different gap scales, not only the reliability of the deformation movement of the deformable structure system is improved, effectively avoiding the occurrence of jamming, but also external load-bearing is guaranteed.

[0014] The beneficial effects of the present invention are as follows:

[0015] 1. The present invention is based on a modular concept to design translational and rotational articulated structures with multi-scale gaps. The deformation structure system has high reliability and a wide range of applications.

[0016] 2. The present invention adopts a translational hinged structure design of a slider and a guide rail combination, the movement process of the telescopic wings is continuous and smooth, and the "drawer-type" structural layout has a strong load-bearing capacity;

[0017] 3. The present invention adopts a rotating hinge structure design of a rotating shaft and a base combination, which makes the folding wing unfolding / folding movement continuous and smooth, and the dual rotating shaft connection form has a strong load-bearing capacity;

[0018] 4. The present invention adopts a power system with two sets of translational servo motors, which has a simple transmission mechanism design, high mechanism reliability, strong control coordination, and low difficulty in analyzing the dynamic characteristics of the nonlinear multi-body system of the mechanism;

[0019] 5. The telescopic wing skin of the present invention is made of high-temperature resistant materials, and the internal frame structure is made of aluminum alloy 3D printing, which has low manufacturing cost and high degree of mass production;

[0020] 6. The folding wing skin of the present invention is made of high-temperature resistant materials, the internal frame beam structure is made of aluminum alloy, and the skin and frame beam structure are processed by an integrated molding process in an embedded manner, so the structure has a strong bearing capacity. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The accompanying drawings, which constitute a part of this application, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an improper limitation of the present invention.

[0022] Figure 1 A deformable structure system for a variant aircraft according to the present invention;

[0023] Figure 2 It is a specific composition of each subsystem according to the present invention;

[0024] Figure 3 is an overall schematic diagram of the deformable structural system according to the present invention;

[0025] Figure 4 is a schematic diagram of the telescopic wing;

[0026] Figure 5 It is a schematic diagram of the folding wings;

[0027] Figure 6 It is a schematic diagram of a translational hinge structure;

[0028] Figure 7 is a schematic diagram of a rotating hinge;

[0029] Figure 8 This is a schematic diagram of the servo motor that drives the telescopic wing translation;

[0030] Figure 9 This is a schematic diagram of the servo motor that drives the folding wing translation;

[0031] Figure 10 This is a schematic diagram of the mounting bracket;

[0032] Figure 11 It is a schematic diagram of the gap scale of the translational hinge structure;

[0033] Figure 12 is a schematic diagram of the initial state of the deformed structure;

[0034] Figure 13 It is a schematic diagram of the final state of the deformed structure.

[0035] Among them: 1-folding wing frame beam structure; 2-telescopic wing frame structure; 3-slider; 4-guide rail; 5-main rotating shaft; 6-transmission mechanism connecting shaft; 7-transmission mechanism; 8-pushing folding wing translation servo motor; 9-translation servo motor mounting bracket 1; 10-translation screw nut; 11-pushing telescopic wing translation servo motor; 12-translation servo motor mounting bracket 2; 13-mounting bracket DETAILED DESCRIPTION

[0036] In order to enable those skilled in the art to better understand the solutions of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts should fall within the scope of protection of the present invention.

[0037] This embodiment provides a spaceflight variant aircraft deformation structure system, the variant aircraft deformation structure system is as follows Figure 1 As shown in the figure, the specific components of each subsystem are as follows: Figure 2 As shown, the entire system is mainly composed of a translational articulated structure, a rotational articulated structure, a translational servo motor, telescopic wings, folding wings, and a mounting support subsystem.

[0038] The translational hinge structure mainly includes a slider 3 and a guide rail 4 .

[0039] The rotating hinge structure mainly includes a main rotating shaft 5, a transmission mechanism connecting shaft 6, and a base.

[0040] The translation servo motors mainly include a translation servo motor 8 for pushing the folding wings and a translation servo motor 11 for pushing the telescopic wings.

[0041] The telescopic wing mainly comprises a skin and a telescopic wing frame structure 2. The skin is made of high-temperature resistant composite material, and the structural form of the skin is omitted in the present invention.

[0042] The base of the rotating hinge structure is located at the front end of the telescopic wing frame structure 2, that is, a hole is opened at the front end of the telescopic wing frame structure 2. The main rotating shaft 5 is matched with the hole at the front end of the telescopic wing frame structure 2.

[0043] The design constraint relationship of the gap size between the main rotating shaft 5 and the hole is as follows:

[0044] Ω ra =100%·min|c / R|

[0045] Wherein R represents the diameter of the main rotating shaft 5, and the minimum normal distance (gap) between the curved surface of the main rotating shaft 5 and the curved surface of the hole is c.

[0046] Through multi-scale gap design, the main rotation axis 5 is adjusted to different gap scales to ensure the continuous and smooth movement of the folding wings. This multi-scale gap design also effectively supports technical advancements such as the study of the dynamic characteristics of nonlinear multi-body systems of gap structures and the optimization of control design for deformable structural systems.

[0047] The folding wing translation servo motor 8 and the telescopic wing translation servo motor 11 are located in the telescopic wing frame structure 2. The folding wing translation servo motor 8 is connected to the transmission mechanism connecting shaft 6 via a transmission mechanism 7. The folding wing translation servo motor 8 is connected to the telescopic wing frame structure 2 via a translation servo motor mounting bracket 1 9, thereby ensuring synchronous movement of the folding wing translation servo motor 8 and the telescopic wing frame structure 2.

[0048] A translation screw nut 10 is mounted on the lead screw of the telescopic wing translation servo motor 11, and the translation screw nut 10 is screw-connected to the telescopic wing frame structure 2. Under the action of the telescopic wing translation servo motor 11, the translation screw nut 10 moves along with the telescopic wing frame structure 2.

[0049] The slider 3 is connected to the telescopic wing frame structure 2 by screws.

[0050] The gap size between the slider 3 and the guide rail 4 is designed with reference to Figure 11 , the constraints are as follows:

[0051] Ω pl =100% min|c / T i | i＝1、2

[0052] It is assumed that the minimum normal distance (gap) between the contact surface of the slider 3 and the contact surface of the guide rail 4 is c, the distance from the bottom end surface of the slider 3 to the contact surface of the guide rail 4 is T1, and the distance from the side end surface of the slider 3 to the central symmetry plane of the guide rail 4 is T2.

[0053] Through multi-scale gap design, the sliding blocks 3 with different gap scales are modified to ensure the continuous and smooth movement of the telescopic wings. This multi-scale gap design also effectively supports technical advancements such as the study of the dynamic characteristics of nonlinear multi-body systems of gap structures and the optimization of control design for deformable structural systems.

[0054] The folding wing mainly includes a skin and a folding wing frame beam structure 1. The skin is made of high-temperature resistant composite material, and the structural form is omitted in the present invention. The folding wing frame beam structure 1 and the skin are processed by an embedded integrated molding process.

[0055] The main rotating shaft 5, the transmission mechanism connecting shaft 6 and the frame beam structure 1 are connected through holes.

[0056] The mounting bracket 13 is mainly used to install the guide rail 4 and is connected to the telescopic wing translation servo motor 11 through the translation servo motor mounting bracket 2 12. At the same time, the other end of the mounting bracket 13 is connected to the fuselage of the aerospace variant aircraft.

[0057] The working principle and process are described in detail below:

[0058] (1) Deformation structure deployment process of aerospace variant vehicles

[0059] The present invention first drives the translation screw nut 10 on the screw by the push telescopic wing translation servo motor 11, and the translation screw nut 10 drives the telescopic wing frame structure 2 to unfold and translate, and the telescopic wing frame structure 2 drives the slider 3 to move linearly along the guide rail 4, and the telescopic wing frame structure 2 drives the translation servo motor mounting support 9 to unfold and move, and the translation servo motor mounting support 9 drives the push folding wing translation servo motor 8 to unfold and move, and the push folding wing translation servo motor 8 drives the transmission mechanism 7 to unfold and move, and the transmission mechanism 7 is driven by the transmission mechanism 7. The mechanism connecting shaft 6 drives the folding wing frame beam structure 1 to unfold, and at the same time, the telescopic wing frame structure 2 drives the folding wing frame beam structure 1 to unfold through the main rotating shaft 5. When the telescopic wing translation servo motor 11 stops working after a certain stroke, the folding wing translation servo motor 8 starts to operate, and drives the transmission mechanism connecting shaft 6 to rotate around the main rotating shaft 5 through the transmission mechanism 7, and finally realizes the folding wing frame beam structure 1 to rotate 900 until it is in the same plane with the telescopic wing frame structure 2. At this time, the folding wing translation servo motor 8 stops working. The final state is as follows Figure 13 shown.

[0060] (2) Recovery process of deformed structures of spaceflight variant vehicles

[0061] The present invention first drives the transmission 7 through the recovery movement of the folding wing translation servo motor 8, and the transmission mechanism 7 pulls the transmission mechanism connecting shaft 6 to rotate around the main rotation axis 5, and finally realizes the folding wing frame beam structure 1 to rotate 900 until it is perpendicular to the telescopic wing frame structure 2. At this time, the folding wing translation servo motor 8 stops working. Then the telescopic wing translation servo motor 11 starts to recover, and drives the telescopic wing frame structure 2 to recover through the translation screw nut 10. The telescopic wing frame structure 2 drives the slider 3 to move linearly along the guide rail 4. The telescopic wing frame structure 2 drives the translation servo motor mounting bracket 9 to recover. The translation servo motor mounting bracket 9 drives the folding wing translation servo motor 8 to recover. The folding wing translation servo motor 8 drives the transmission mechanism 7 to recover. The transmission mechanism 7 drives the folding wing frame beam structure 1 to recover through the transmission mechanism connecting shaft 6. At the same time, the telescopic wing frame structure 2 drives the folding wing frame beam structure 1 to recover through the main rotating shaft 5. When the telescopic wing translation servo motor 11 moves a certain stroke, it stops working. The final state is as follows. Figure 12 shown.

[0062] The above description of the disclosed embodiments is intended to enable one skilled in the art to implement or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the scope of the present invention. Therefore, the present invention is not limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A deformable structure system for aerospace deformable aircraft, characterized in that: The system comprises: a translation hinge structure, a rotation hinge structure, a translation servo motor, a telescopic wing, a folding wing, and a mounting support; The translational hinge structure envelops a slider (3) and a guide rail (4); The rotating hinge structure comprises a main rotating shaft (5), a transmission mechanism connecting shaft (6), and a base; The translation servo motor comprises a translation servo motor (8) for driving the folding wings and a translation servo motor (11) for driving the telescopic wings; The folding wing comprises a skin and a folding wing frame beam structure (1); The telescopic wing comprises a skin and a telescopic wing frame structure (2); The base of the rotating hinge structure is located at the front end of the telescopic wing frame structure (2), that is, a hole is opened at the front end of the telescopic wing frame structure (2), and the main rotating shaft (5) cooperates with the hole opened at the front end of the telescopic wing frame structure (2).

2. The aerospace deformable aircraft deformable structure system according to claim 1, characterized in that: The gap between the slider and the guide rail is based on the gap scale formula, and the slider can achieve multi-scale clearance fit.

3. The aerospace deformable aircraft deformable structure system according to claim 2, characterized in that: The gap scale formula is Ω pl =100% min|c / T i | i＝1、2 , Wherein, c is the minimum normal dimension between the contact surface of the slider (3) and the contact surface of the guide rail (4), T1 is the distance from the bottom end surface of the slider (3) to the contact surface of the guide rail (4), and T2 is the distance from the side end surface of the slider (3) to the central symmetry plane of the guide rail (4).

4. The aerospace deformable aircraft deformable structure system according to claim 1, characterized in that: The gap size between the main rotating shaft (5) and the hole is Ω ra =100% min|c / R|, Wherein, R represents the diameter of the main rotating shaft (5), and c represents the minimum normal gap size between the curved surface of the main rotating shaft (5) and the curved surface of the hole.

5. The aerospace deformable aircraft deformable structure system according to claim 1, characterized in that: The servo motor (8) for pushing the folding wing translation and the servo motor (11) for pushing the telescopic wing translation are located in the telescopic wing frame structure (2).

6. The aerospace deformable aircraft deformable structure system according to claim 1, characterized in that: The folding wing translation servo motor (8) is connected to the telescopic wing frame structure (2) via a translation servo motor mounting bracket (9), thereby ensuring that the folding wing translation servo motor (8) and the telescopic wing frame structure (2) move synchronously.

7. The aerospace deformable aircraft deformable structure system according to claim 1, characterized in that: The folding wing adopts an assembled connecting rod skeleton structure, and the connecting rods are connected by hinges. The skeleton structure can complete the folding or unfolding action under the drive of the wing actuating motor.

8. The aerospace deformable aircraft deformable structure system according to claim 7, characterized in that: The skin is made of high-temperature resistant composite material.

9. The aerospace deformable aircraft deformable structure system according to any one of claims 1 to 8, characterized in that: The expansion process is: The telescopic wing translation servo motor (11) is actuated to drive the translation screw nut (10) on the screw to translate, and the translation screw nut (10) drives the telescopic wing frame structure (2) to unfold and translate, and the telescopic wing frame structure (2) drives the slider (3) to move linearly along the guide rail (4), and the telescopic wing frame structure (2) drives the translation servo motor mounting support (9) to unfold and move, and the translation servo motor mounting support (9) drives the folding wing translation servo motor (8) to unfold and move, and the folding wing translation servo motor (8) drives the transmission mechanism (7) to unfold and move. The transmission mechanism (7) drives the folding wing frame beam structure (1) to unfold through the transmission mechanism connecting shaft (6), and at the same time, the telescopic wing frame structure (2) drives the folding wing frame beam structure (1) to unfold through the main rotating shaft (5). When the servo motor (11) that promotes the translation of the telescopic wing stops working after a certain stroke, the servo motor (8) that promotes the translation of the folding wing starts to operate and drives the transmission mechanism connecting shaft (6) to rotate around the main rotating shaft (5), and finally the folding wing frame beam structure (1) is rotated 90 degrees. 0 Until it is in the same plane as the telescopic wing frame structure (2), at which time the servo motor (8) that pushes the folding wing translation stops working.

10. The aerospace deformable aircraft deformable structure system according to any one of claims 1 to 9, characterized in that: The recycling process is: The folding wing translation servo motor (8) retracts and drives the transmission mechanism (7), and the transmission mechanism (7) pulls the transmission mechanism connecting shaft (6) to rotate around the main rotation axis (5), ultimately achieving the folding wing frame beam structure (1) to rotate 90 degrees. 0 Until it is perpendicular to the telescopic wing frame structure (2), at which time the folding wing translation servo motor (8) stops working; then the telescopic wing translation servo motor (11) starts to recover, and drives the telescopic wing frame structure (2) to start recovery through the translation screw nut (10), the telescopic wing frame structure (2) drives the slider (3) to move linearly along the guide rail (4), the telescopic wing frame structure (2) drives the translation servo motor mounting support (9) to recover, the translation servo motor mounting support (9) drives the folding wing translation servo motor (8) to recover, the folding wing translation servo motor (8) drives the transmission mechanism (7) to recover, the transmission mechanism (7) drives the folding wing frame beam structure (1) to recover through the transmission mechanism connecting shaft (6), and at the same time, the telescopic wing frame structure (2) drives the folding wing frame beam structure (1) to recover through the main rotating shaft (5), and stops working after the telescopic wing translation servo motor (11) moves a certain stroke.

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