Split annular fixing structure for load of hypersonic aircraft

Abstract

The invention provides a hypersonic aircraft load split annular fixing structure which is used for fixing a load in a cabin and comprises a main supporting ring, a first supporting ring, a second supporting ring and a third supporting ring, and the first supporting ring, the second supporting ring and the third supporting ring are sequentially distributed in the axial direction of the load. The peripheries of the three are respectively fixed with the cabin body; the main supporting ring is fixedly arranged on the periphery of a load in a sleeving mode, the inner periphery of the first supporting ring abuts against the periphery of the main supporting ring, the inner periphery of the second supporting ring is fixed to the periphery of the main supporting ring, the third supporting ring is arranged on the load in a sleeving mode, a pressing plate is fixed to the inner periphery of the third supporting ring, and the pressing plate is fixed to the axial end of the load through a first connecting piece. By the adoption of the split type annular structure, each supporting ring can have a relatively independent deformation space under the severe temperature gradient, the stress concentration problem in an integrated structure is avoided, meanwhile, each supporting ring can be independently machined and sequentially installed on a load and a cabin body, the operation process is simplified, and replacement and maintenance are convenient.

Description

Technical Field

[0001] This application relates to the field of hypersonic vehicle payload systems, and in particular to a split-ring fixed structure for hypersonic vehicle payloads. Background Technology

[0002] With the iterative upgrades of aerospace technology, hypersonic vehicles (flying at Mach number Ma>5) have become a core development direction in both military and civilian fields due to their advantages such as ultra-long range and strong penetration capabilities. Their payload capacity directly determines mission effectiveness. These vehicles need to stably fix various payloads such as sensors and munitions, but the extreme environment and performance constraints of hypersonic flight pose severe challenges to payload installation and fixation structures, and traditional technologies are no longer sufficient to meet the requirements.

[0003] Hypersonic flight presents multiple extreme challenges: aerodynamic heating causes surface temperatures to rise instantly to 600-800 degrees Celsius, with local short-term temperature gradients reaching 700 K / cm. Differences in thermal expansion between different materials can easily lead to structural cracks or compression damage. Long-term effects of strong vibrations (total root mean square magnitude exceeding 20g) and noise (exceeding 165dB) can cause problems such as loose bolts and weld fatigue. At the moment of load separation, the system may even face instantaneous loads exceeding 100g. Complex aerodynamic forces and shock wave interference further exacerbate structural stress and affect the reliability of the fixation.

[0004] Currently, hypersonic technology is at a bottleneck stage, and the reliability of the fixed load structure has become a key factor restricting the engineering application of aircraft. Existing fixed structures usually adopt an integrated rigid design, which is difficult to adapt to the severe temperature changes and vibration impacts under hypersonic flight conditions. This can easily lead to stress concentration, resulting in problems such as loose connections and structural damage, and poor stability. Summary of the Invention

[0005] The purpose of this application is to address the above problems by providing a split-ring fixing structure for the payload of a hypersonic aircraft, used to fix the payload within the cabin. The fixing structure includes: The main support ring is sleeved and fixed on the outer periphery of the load; The first support ring has its inner circumference abutting against the outer circumference of the main support ring. The second support ring, the inner circumference of which is fixed to the outer circumference of the main support ring, is used to provide radial support force to the load. A third support ring is fitted onto the load. A pressure plate is fixed to the inner circumference of the third support ring. The pressure plate is fixed to the axial end of the load through a first connector. The third support ring is used to cooperate with the first support ring to provide axial support force to the load. The first support ring, the second support ring, and the third support ring are distributed sequentially along the axial direction of the load, and their outer peripheries are respectively fixed to the cabin body.

[0006] According to certain embodiments of the present application, the technical solutions provided are as follows: The outer periphery of the main support ring is provided with a first abutting portion extending radially therefrom, and the outer diameter of the first abutting portion gradually increases towards the third support ring along the axial direction of the load. The inner circumference of the first support ring is provided with a second abutment portion extending radially therefrom, and the inner circumferential contour of the second abutment portion matches the outer circumferential contour of the first abutment portion.

[0007] According to certain embodiments of the present application, the technical solutions provided are as follows: The outer periphery of the main support ring is provided with a first connecting portion extending radially therefrom; The inner circumference of the second support ring is provided with a second connecting portion extending radially therefrom, and the second connecting portion is fixedly connected to the first connecting portion.

[0008] According to the technical solutions provided in certain embodiments of this application, there is a first gap between the pressure plate and the axial end of the load, and the first gap is filled with a gasket.

[0009] According to the technical solutions provided in certain embodiments of this application, there is a second gap between the inner periphery of the second connecting portion and the outer periphery of the main support ring.

[0010] According to the technical solutions provided in certain embodiments of this application, the main support ring is threadedly connected to the load and fixed to the load through a second connector.

[0011] According to the technical solutions provided in certain embodiments of this application, the first support ring, the second support ring and the third support ring are all provided with a plurality of fan-shaped holes, which are used to reduce the weight of the fixing structure.

[0012] According to the technical solutions provided in certain embodiments of this application, the first support ring, the second support ring and the third support ring are all provided with clearance grooves, which are used to avoid structures inside the cabin.

[0013] Compared with the prior art, the beneficial effects of this application are as follows: This application provides a split ring-shaped fixing structure for a hypersonic vehicle payload, used to fix the payload within the cabin. The fixing structure includes a main support ring, a first support ring, a second support ring, and a third support ring. The first support ring, the second support ring, and the third support ring are distributed sequentially along the axial direction of the payload, and their outer peripheries are respectively fixed to the cabin. The main support ring is sleeved and fixed to the outer periphery of the payload. The inner periphery of the first support ring abuts against the outer periphery of the main support ring. The inner periphery of the second support ring is fixed to the outer periphery of the main support ring, used to provide radial support force to the payload. The third support ring is sleeved on the payload. A pressure plate is fixed to the inner periphery of the third support ring. The pressure plate is fixed to the axial end of the payload through a first connector. The third support ring is used to cooperate with the first support ring to provide axial support force to the payload. By adopting a split ring structure, each support ring can have a relatively independent deformation space under the severe temperature gradient generated by hypersonic flight, avoiding the stress concentration problem caused by the difference in thermal expansion coefficient in the integrated structure, thereby reducing the risk of structural cracks or extrusion damage and improving the long-term reliability of the fixed structure under thermal cycling. Compared to an integrated structure, the split ring structure has advantages in manufacturing, assembly, disassembly and maintenance. Each support ring can be processed and inspected independently, and then installed onto the load and the cabin in sequence, simplifying the operation process and facilitating replacement and maintenance.

[0014] It should be understood that the descriptions of technical features, technical solutions, beneficial effects, or similar language in this application do not imply that all features and advantages can be achieved in any single embodiment. Rather, it is understood that the description of a feature or beneficial effect means that a specific technical feature, technical solution, or beneficial effect is included in at least one embodiment. Therefore, the descriptions of technical features, technical solutions, or beneficial effects in this specification do not necessarily refer to the same embodiment. Furthermore, the technical features, technical solutions, and beneficial effects described in this embodiment can be combined in any suitable manner. Those skilled in the art will understand that embodiments can be implemented without one or more specific technical features, technical solutions, or beneficial effects of a particular embodiment. In other embodiments, additional technical features and beneficial effects may be identified in specific embodiments that do not embody all embodiments. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1This application provides a schematic diagram of a split-ring fixed structure for the payload of a hypersonic vehicle. Figure 2 A schematic diagram of the main support ring, the first support ring, and the second support ring of a hypersonic vehicle payload split-ring fixing structure provided in this application embodiment; Figure 3 A schematic diagram of the third support ring of a split-ring fixing structure for the payload of a hypersonic vehicle provided in this application embodiment; Figure 4 This is a cross-sectional schematic diagram of the main support ring, the first support ring, and the second support ring of a hypersonic vehicle payload split-ring fixing structure provided in an embodiment of this application.

[0017] The text labels in the image represent: 1. Main support ring; 2. First support ring; 3. Second support ring; 4. Third support ring; 5. Pressure plate; 6. Gasket; 7. Load; 11. First abutment part; 12. First connecting part; 21. Second abutment part; 31. Second connecting part; 101. Fan-shaped hole; 102. Clearance groove. Detailed Implementation

[0018] To enable those skilled in the art to better understand the technical solutions of this application, the technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. The descriptions in this section are merely illustrative and explanatory, and should not be construed as limiting the scope of protection of this application. Specifically, the described embodiments are only some embodiments of this application, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort should fall within the scope of protection of this invention.

[0019] It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such process, method, product, or apparatus.

[0020] As mentioned in the background section, to address the problems existing in the prior art, this embodiment provides a hypersonic vehicle payload split-ring fixing structure for fixing the payload 7 within the cabin. The fixing structure includes: Main support ring 1, the main support ring 1 is sleeved and fixed on the outer periphery of load 7; The inner circumference of the first support ring 2 abuts against the outer circumference of the main support ring 1; The second support ring 3, the inner circumference of the second support ring 3 is fixed to the outer circumference of the main support ring 1, and is used to provide radial support force to the load 7. The third support ring 4 is sleeved on the load 7. A pressure plate 5 is fixed to the inner circumference of the third support ring 4. The pressure plate 5 is fixed to the axial end of the load 7 through the first connecting piece. The third support ring 4 is used to cooperate with the first support ring 2 to provide axial support force to the load 7. The first support ring 2, the second support ring 3, and the third support ring 4 are distributed sequentially along the axial direction of the load 7, and their outer peripheries are fixed to the cabin body respectively.

[0021] like Figure 1-4 As shown, in this embodiment, the load 7 is approximately cylindrical or conical in shape, with threads forming its outer periphery. The main support ring 1 is approximately cylindrical in shape, with threads forming its inner periphery as well. The main support ring 1 can be fitted onto the outer periphery of the load 7 and threadedly engaged with it. It is also fixed by a second connector, which can be a bolt (as in the prior art) and is arranged radially along the load 7. The first support ring 2, the second support ring 3, and the third support ring 4 have partially identical structures, each including an inner circle, a main body, and an outer circle connected radially. Several first fixing members are distributed circumferentially on the outer circles of the three support rings. These first fixing members are arranged radially along the load 7. The three support rings are respectively fixed to the cabin by the first fixing members. Further, the first fixing members can be M8 screws (as in the prior art), and there are 24 first fixing members. The inner circle of the support ring 2 is surface-fitted with the outer circumference of the main support ring 1, allowing it to abut and be fixed to the outer circumference of the main support ring 1. Several second fixing members are distributed circumferentially on the inner circle of the second support ring 3. These second fixing members are arranged along the axial direction of the load 7. The second support ring 3 is fixed to the main support ring 1 via these second fixing members. Furthermore, the second fixing members can also be M8 screws as used in the prior art. There are 18 second fixing members. The inner circle of the third support ring 4 is provided with the same number of second fixing members as the second support ring 3. The third support ring 4 is fixed to the pressure plate 5 via these second fixing members. The pressure plate 5 is fixed to the axial end of the load 7 via a first connecting member. The first connecting member can be a bolt as used in the prior art and is arranged along the axial direction of the load 7. Furthermore, four shear bosses are also provided inside the compartment. These shear bosses provide support for the third support ring 4 along the axial direction of the load 7.

[0022] In use, the first support ring 2 and the second support ring 3 are sequentially fixed in the cabin along the axial direction of the load 7. Then, the main support ring 1 passes through the second support ring 3 so that the main support ring 1 abuts against the first support ring 2. The main support ring 1 and the second support ring 3 are fixed by the second fastener. The third support ring 4 is fixed in the cabin, located on the side of the second support ring 3 away from the first support ring 2. The load 7 passes through the third support ring 4 and the main support ring 1. At the same time, the load 7 is threadedly connected to the main support ring 1. The main support ring 1 and the load 7 are fixed by the second connector. The pressure plate 5 is fixed to the third support ring 4 by the second fastener. The pressure plate 5 is fixed to the axial end of the load 7 by the first connector, so that the first support ring 2 and the third support ring 4 cooperate with each other to provide support force for the load 7 along the axial direction of the load 7.

[0023] By adopting a split ring structure, each support ring can have a relatively independent deformation space under the severe temperature gradient generated by hypersonic flight, avoiding the stress concentration problem caused by the difference in thermal expansion coefficient in the integrated structure, thereby reducing the risk of structural cracks or extrusion damage and improving the long-term reliability of the fixed structure under thermal cycling. Compared to an integrated structure, the split ring structure has advantages in manufacturing, assembly, disassembly and maintenance. Each support ring can be processed and inspected independently and then installed onto the load 7 and the cabin in sequence, which simplifies the operation process and facilitates replacement and maintenance. The split-type ring structure itself has certain damping characteristics and deformation coordination capabilities. When the aircraft experiences high-intensity vibration and instantaneous high overload, the kinetic energy and impact force of load 7 can be dispersed and dissipated through the interaction of multiple ring support surfaces, small relative displacement or elastic deformation, which helps to alleviate the fatigue of bolts, screws and other connecting parts and reduce the risk of loosening. By decoupling radial and axial support functions onto different components, independent structural optimization can be performed for load characteristics in different directions, thereby more effectively resisting complex multi-directional loads and shock wave interference during hypersonic flight and improving fixation stability.

[0024] Furthermore, there is a first gap between the pressure plate 5 and the axial end of the load 7, and the first gap is filled with a gasket 6; For details, please refer to Figure 3By filling the first gap with a shim 6, the elasticity of the shim 6 can be used to adjust the assembly gap in the axial direction of the load 7, ensuring that the pressure plate 5 can cooperate with the first support ring 2 to provide a stable axial clamping force to the load 7. The length of the first gap along the axial direction of the load 7 is 3mm, and the axial thickness of the shim 6 is 1mm. By adding or removing shims 6, the overall thickness of multiple shims 6 can be adjusted, which can effectively control the magnitude of the axial preload and avoid stress concentration in the structure due to excessive tightness or loosening due to excessive looseness during vibration. The shim 6 can provide deformation margin during thermal expansion, absorb dimensional differences caused by temperature changes, reduce thermal stress accumulation, and also play a damping and buffering role, absorbing some vibration energy and reducing impact transmission.

[0025] Furthermore, the first support ring 2, the second support ring 3 and the third support ring 4 are each provided with a plurality of fan-shaped holes 101, which are used to reduce the weight of the fixing structure. For details, please refer to Figure 2 and Figure 3 The main body of the first support ring 2, the second support ring 3 and the third support ring 4 are all provided with fan-shaped holes 101. Multiple fan-shaped holes 101 are distributed along the circumference of the main body, so that the support rings form a hollow design, which effectively reduces the weight of the support rings and meets the lightweight design requirements of hypersonic aircraft.

[0026] Furthermore, the first support ring 2, the second support ring 3 and the third support ring 4 are all provided with clearance grooves 102, which are used to avoid structures inside the cabin. For details, please refer to Figure 2 and Figure 3 The outer circumferences of the first support ring 2, the second support ring 3 and the third support ring 4 have breaks. The breaks and the corresponding fan-shaped holes 101 together form a clearance groove 102. The clearance groove 102 can effectively avoid the structure inside the cabin and prevent the support ring from interfering with the cabin structure.

[0027] In a preferred embodiment, The outer periphery of the main support ring 1 is provided with a first abutting portion 11 that extends radially therefrom, and the outer diameter of the first abutting portion 11 gradually increases towards the side closer to the third support ring 4 along the axial direction of the load 7. The inner circumference of the first support ring 2 is provided with a second abutting portion 21 extending radially therefrom, and the inner circumferential contour of the second abutting portion 21 matches the outer circumferential contour of the first abutting portion 11.

[0028] like Figure 4As shown, both the first abutment part 11 and the second abutment part 21 are annular structures. The outer circumferential surface of the first abutment part 11 and the inner circumferential surface of the second abutment part 21 are conical end faces, and their contours match each other. When the main support ring 1 is inserted into the first support ring 2 along the axial direction, the conical surfaces between the first abutment part 11 and the second abutment part 21 can cooperate to fix the main support ring 1 and the first support ring 2 together. The conical mating surface allows for a small relative displacement along the axial direction at high temperatures, which can avoid the huge internal stress caused by the obstruction of thermal expansion. At the same time, the conical mating surface can convert part of the axial support force into radial clamping force, enhance the friction and connection stability of the contact surface, and form a more continuous force transmission path, which is beneficial to maintaining the integrity of the structure in vibration and thermal cycling. The conical mating surface has self-centering characteristics, which can guide the main support ring 1 and the first support ring 2 to automatically align during the assembly process, reducing the assembly difficulty.

[0029] In a preferred embodiment, The outer periphery of the main support ring 1 is provided with a first connecting portion 12 extending radially therefrom; The inner circumference of the second support ring 3 is provided with a second connecting portion 31 that extends radially therefrom, and the second connecting portion 31 is fixedly connected to the first connecting portion 12.

[0030] like Figure 4 As shown, both the first connecting part 12 and the second connecting part 31 are annular structures. The first connecting part 12 is located on the outer periphery of the main support ring 1 and has multiple connecting holes. The second connecting part 31 is located on the inner circle of the second support ring 3 and has multiple second fixing members. By passing the second fixing members through the connecting holes along the axial direction of the load 7 and engaging with the nut, the main support ring 1 and the second support ring 3 can be fixed.

[0031] Furthermore, there is a second gap between the inner periphery of the second connecting portion 31 and the outer periphery of the main support ring 1.

[0032] Specifically, by providing a second gap between the inner circumference of the second connecting portion 31 and the outer circumference of the main support ring 1, the second support ring 3 can avoid limiting interference with the main support ring 1 in the axial direction of the load 7, ensuring that after the pressure plate 5 is connected to the axial end of the load 7, the first abutting portion 11 of the main support ring 1 can be pressed and fitted with the second abutting portion 21 of the first support ring 2; optionally, the width of the second gap along the radial direction of the load 7 is 1 mm.

[0033] Working principle: In use, the first support ring 2 and the second support ring 3 are fixed sequentially in the cabin along the axial direction of the load 7. Then, the main support ring 1 passes through the second support ring 3, so that the first abutting part 11 of the main support ring 1 and the second abutting part 21 of the first support ring 2 press against each other. The main support ring 1 and the second support ring 3 are fixed by the second fixing member. The third support ring 4 is fixed in the cabin, and the third support ring 4 is located on the side of the second support ring 3 away from the first support ring 2. The load 7 passes through the third support ring 4 and the main support ring 1. At the same time, the load 7 is threadedly connected to the main support ring 1. The main support ring 1 and the load 7 are fixed by the second connecting member. A shim 6 is placed on the axial end of the load 7 near the third support ring 4. The pressure plate 5 is fixed to the third support ring 4 by the second fixing member. The pressure plate 5 is fixed to the axial end of the load 7 by the first connecting member, so that the first support ring 2 and the third support ring 4 cooperate with each other. At the same time, the pressure plate 5 presses the shim 6. Thus, the load 7 is fixed.

[0034] This document uses specific examples to illustrate the principles and implementation methods of this application. The descriptions of the above embodiments are only for the purpose of helping to understand the methods and core ideas of this application. The above descriptions are only preferred embodiments of this application. It should be noted that due to the limitations of written expression, while there are objectively infinite specific structures, those skilled in the art can make several improvements, modifications, or changes without departing from the principles of this invention, and can also combine the above technical features in an appropriate manner. These improvements, modifications, changes, or combinations, or the direct application of the inventive concept and technical solution to other situations without modification, should all be considered within the scope of protection of this application.

Claims

1. A high supersonic vehicle load split toroidal fixation structure for fixing a load (7) inside a capsule, characterized in that, The fixing structure comprises: a main support ring (1) fixedly sleeved on the outer periphery of the load (7); a first support ring (2) with the inner periphery abutting against the outer periphery of the main support ring (1); a second support ring (3) with the inner periphery fixedly sleeved on the outer periphery of the main support ring (1) and used for providing a radial support force to the load (7); a third support ring (4) sleeved on the load (7) and having a pressing plate (5) fixedly sleeved on the inner periphery, the pressing plate (5) being fixed to the axial end of the load (7) through a first connecting member, the third support ring (4) being used for cooperating with the first support ring (2) to provide an axial support force to the load (7); the first support ring (2), the second support ring (3) and the third support ring (4) are sequentially arranged along the axial direction of the load (7), and the outer peripheries of the three are fixed to the cabin body.

2. The load split annular fixing structure of the hypersonic aircraft according to claim 1, wherein the outer periphery of the main support ring (1) is provided with a first abutting portion (11) extending in the radial direction, and the outer diameter of the first abutting portion (11) gradually increases along the axial direction of the load (7) towards the side close to the third support ring (4); the inner periphery of the first support ring (2) is provided with a second abutting portion (21) extending in the radial direction, and the inner periphery contour of the second abutting portion (21) matches the outer periphery contour of the first abutting portion (11).

3. The load split annular fixing structure of the hypersonic aircraft according to claim 1, wherein the outer periphery of the main support ring (1) is provided with a first connecting portion (12) extending in the radial direction; the inner periphery of the second support ring (3) is provided with a second connecting portion (31) extending in the radial direction, and the second connecting portion (31) is fixedly connected with the first connecting portion (12).

4. The high supersonic vehicle load dividing ring fixing structure according to claim 1, characterized in that, a first gap is formed between the pressing plate (5) and the axial end of the load (7), and the first gap is filled with a gasket (6).

5. The high supersonic vehicle load dividing ring fixing structure according to claim 3, wherein a second gap is formed between the inner periphery of the second connecting portion and the outer periphery of the main support ring (1).

6. The high supersonic vehicle load dividing ring fixing structure according to claim 1, wherein the main support ring (1) is threadedly connected to the load (7) and is fixed to the load (7) through a second connecting member.

7. The high supersonic vehicle load dividing ring fixing structure according to claim 1, wherein the first support ring (2), the second support ring (3) and the third support ring (4) are each provided with a plurality of fan-shaped holes (101) for reducing the weight of the fixing structure.

8. The high supersonic vehicle load dividing ring fixing structure according to claim 1, wherein the first support ring (2), the second support ring (3) and the third support ring (4) are each provided with an avoiding groove (102) for avoiding the structures in the cabin body.

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