A morphing fuselage structure for hypersonic environments

Abstract

The application belongs to the technical field of variable aircraft structure design, and particularly relates to a deformable fuselage structure for a hypersonic environment, which comprises a deformable fuselage frame and a deformable fuselage skin; the deformable fuselage frame comprises a sliding groove section, a sliding key section, a corrugated beam, a variable-height support column and a variable-length support rod; the corrugated beam is arranged on the outer side of the sliding key section and the sliding groove section, and has a wave crest and a wave trough structure; the sliding key section and the sliding groove section are arranged on the inner side of the corrugated beam and are spaced apart, and are staggered; the deformable fuselage skin comprises a deformable support framework, a sliding scale and an S-shaped heat insulation plate; the fuselage shape and the cross-sectional size can be greatly changed by control, so that the large-size fuselage can provide sufficient space to carry more fuel, the small-size fuselage cross section can reduce the flight resistance, improve the fuel utilization rate, the heat insulation skin can block the transfer of aerodynamic heat to the fuselage interior, and the deformable fuselage structure is easy to realize based on existing materials and mature technology.

Description

Technical Field

[0001] This application belongs to the field of deformable aircraft structural design technology, and in particular relates to a deformable fuselage structure for hypersonic environments. Background Technology

[0002] Many aircraft performing round-trip missions need to carry as much fuel as possible at launch to extend their range, requiring a relatively large fuselage size. As fuel is consumed and flight speed increases, the drag generated by the large fuselage becomes an additional burden. Therefore, a deformable fuselage structure is needed, where the fuselage size can be reduced accordingly as fuel is consumed, thereby reducing flight drag and improving fuel efficiency. If the flight speed reaches the hypersonic range, the heat generated by airflow friction must also be considered, preventing excessively high temperatures inside the fuselage and isolating aerodynamic heat outside the fuselage. Current research on deformable structures mostly focuses on wing deformation, with limited research on fuselage variants. Some structural schemes based on unit cell assembly have complex shape control, making them inconvenient for practical applications.

[0003] Therefore, how to achieve effective variability of the fuselage structure is a problem that needs to be solved. Summary of the Invention

[0004] The purpose of this application is to provide a deformable fuselage structure for hypersonic environments, in order to solve the problem that existing deformable structures have not effectively studied fuselage deformation.

[0005] The technical solution of this application is: a deformable fuselage structure for hypersonic environments, comprising a deformable fuselage frame and a deformable fuselage skin; the deformable fuselage frame includes a sliding groove section, a sliding key section, a corrugated beam, a variable-height support column, and a variable-length support rod; the corrugated beam is located outside the sliding key section and the sliding groove section, and the corrugated beam has a crest and trough structure; the sliding key section and the sliding groove section are located inside the corrugated beam and are spaced apart, with the sliding key section and the sliding groove section being staggered; the corrugated beam, the sliding key section, and the sliding groove section are all arc-shaped structures, and the crests and troughs of the corrugated beam are arranged along the radial direction of the arc-shaped structure; the sliding key section and the sliding groove section are nested together to form an arc-shaped support slide, and the troughs of the corrugated beam slide on the arc-shaped support slide;

[0006] The deformable fuselage skin includes a deformable support frame, sliding scales, and S-shaped heat insulation plates; there are multiple sets of sliding scales, which are arranged side by side on the outside of the deformable support frame; the cross-section of the S-shaped heat insulation plate is S-shaped; there are multiple S-shaped heat insulation plates, which are spaced apart between adjacent sliding scales, and adjacent sliding scales are slidably fitted together; the deformable support frame is located inside the sliding scales and the S-shaped heat insulation plates.

[0007] The outer surface formed by the crests of the corrugated beam is connected to the deformable support frame; the corrugated beam and the deformable support frame can deform synchronously.

[0008] Preferably, the variable height support column and the variable length support rod are hinged to both ends of the slide section; both the variable height support column and the variable length support rod are height-adjustable, and the adjustment direction is radial to the arc-shaped support slide.

[0009] The deformable support frame includes multiple elastic plates, which are arranged parallel to the fuselage axis and connected to each other. The length of each elastic plate is equivalent to the distance between the fuselage frames. Each elastic plate has a connecting plate and a flexural plate staggered along its length. The upper edge of the connecting plate is connected to the sliding scale.

[0010] Both the S-shaped heat insulation plate and the elastic plate are made of elastic material. When the shape of the fuselage changes, the sliding scales and the S-shaped heat insulation plate can deform uniformly along with the elastic plate.

[0011] Preferably, the flexural plate includes an upper flexural plate and a lower flexural plate, the lower edge of the connecting plate is on the same straight line as the lower edge of the lower flexural plate, the upper edge of the connecting plate is higher than the upper edge of the upper flexural plate, and the upper edge of the connecting plate is connected to the sliding scales; the upper flexural plate and the lower flexural plate have opposite flexural directions on the vertical plate surface; the flexural plates on the same level and connected to both sides of the connecting plate have opposite flexural directions.

[0012] Preferably, the flexural plates on adjacent elastic plates are welded together, and the connecting plate is integrally formed with the flexural plates on different layers to form a double-layer deformable support frame.

[0013] Preferably, it also includes reinforcing ribs, which are arranged in multiple sets at intervals along the circumference of the deformable fuselage frame. The flexural plate of the deformable support frame is welded to the adjacent reinforcing ribs, and the elastic plate of the deformable support frame is connected to the crest of the corrugated beam of the deformable fuselage frame.

[0014] Preferably, the sliding scale includes a horizontal plate and a vertical plate. The horizontal plate is arranged along a direction perpendicular to the fuselage axis, and the vertical plate is integrally and vertically connected to the middle position of the horizontal plate. The cross-section of the horizontal plate and the vertical plate is T-shaped, and the cross-section of the horizontal plate is stepped. The upper layer of the horizontal plate slides in conjunction with the lower layer of the horizontal plate in the adjacent sliding scale, and the lower layer of the horizontal plate slides in conjunction with the upper layer of the horizontal plate in the adjacent sliding scale.

[0015] Preferably, the cross-section of the sliding key segment is dovetail-shaped, and the middle of the sliding groove segment is provided with a dovetail groove that mates with the sliding key segment; both the upper bottom surfaces of the sliding key segment and the sliding groove segment are provided with reinforcing ribs.

[0016] Preferably, the reinforcing ribs of the keyway section and the groove section are distributed in the middle and on both sides, respectively, and the upper bottom surfaces of the keyway section and the groove section are on the same plane, forming a support rail that can slide with the corrugated beam; the troughs of the corrugated beam are provided with support pulleys at the positions corresponding to the support rails; each trough of the corrugated beam slides on the support rail through the support pulleys.

[0017] Preferably, the supporting pulley includes a pulley seat and sliding rollers. There are three sets of sliding rollers, each corresponding to one of the three sets of reinforcing ribs. Adjacent sliding rollers are connected by axles. The middle sliding roller is correspondingly arranged with the supporting slide rail on the keyway. The upper end of the pulley seat is bolted to the corrugated beam, and the lower end is slidably engaged with the axle of the sliding roller.

[0018] Preferably, the variable height support column includes a shell, a series of butterfly-shaped flexible devices, and a driving device; the shell is a regular hexagon with a hollow internal structure and an open top; the series of butterfly-shaped flexible devices and the driving device are both located inside the shell; the series of butterfly-shaped flexible devices includes multiple sets of vertically stacked flexible plates, each with a central hole, and the flexible plates are coaxially arranged with the shell; the driving device is coaxially arranged with the shell, with its upper end extending from the top opening of the shell and its middle part inserted into the center of the flexible plate; the shell includes multiple sections of column, which are arranged vertically, with adjacent sections nested and slidingly fitted together.

[0019] The deformable fuselage structure for hypersonic environments described in this application can be significantly altered by controlling the shape and cross-sectional dimensions of the fuselage. This allows for a large fuselage to provide sufficient space to carry more fuel, while a small fuselage cross-section reduces flight drag and improves fuel efficiency. The heat-insulating skin prevents aerodynamic heat from being transferred to the interior of the fuselage. Based on existing materials and mature processes, this technology is easy to implement. Attached Figure Description

[0020] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0021] Figure 1 This is a schematic diagram of the overall structure of this application;

[0022] Figure 2 for Figure 1 Cross-sectional view of section A in the middle;

[0023] Figure 3 for Figure 1 Sectional view of section B in the middle;

[0024] Figure 4 This is a schematic diagram of the overall structure of the deformable support frame of this application;

[0025] Figure 5 This is a schematic diagram of the flexural structure of the flexural plate in this application;

[0026] Figure 6 This is a schematic diagram of the flexural network in this application;

[0027] Figure 7 This is an exploded sectional view of the slide section and the keyway section of this application;

[0028] Figure 8 This is a sectional view of the connection structure between the slide section and the key section in this application;

[0029] Figure 9 This is a schematic diagram of the connection structure between the supporting pulley and the corrugated beam in this application;

[0030] Figure 10 This is a schematic diagram of the pulley connection structure supporting this application;

[0031] Figure 11 This is a schematic diagram of the variable height support column structure of this application.

[0032] 1. Slide section; 2. Keyway section; 3. Corrugated beam; 4. Variable height support column; 5. Variable length support rod; 6. Support slide rail; 7. Support pulley; 8. Pulley seat; 9. Sliding roller; 10. Axle; 11. Fork lug; 13. Sliding scale; 14. S-shaped heat insulation board; 15. Elastic plate; 16. Connecting plate; 17. Upper flexible plate; 18. Lower flexible plate; 19. Outer shell; 20. Series butterfly flexible device; 21. Drive device; 22. Column. Detailed Implementation

[0033] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0034] A deformable fuselage structure for hypersonic environments, such as Figures 1-3The system includes a deformable fuselage frame and a deformable fuselage skin. The deformable fuselage frame includes a slide section 1, a slide key section 2, a corrugated beam 3, a variable-height support column 4, and a variable-length support rod 5. The corrugated beam 3 is located outside the slide key section 2 and the slide key section 1, and has a crest and trough structure. The slide key section 2 and the slide key section 1 are located inside the corrugated beam 3 and are spaced apart, with the slide key section 2 and the slide key section 1 being staggered. The corrugated beam 3, the slide key section 2, and the slide key section 1 are all arc-shaped structures, and the crests and troughs of the corrugated beam 3 are arranged along the radial direction of the arc-shaped structure. The slide key section 2 and the slide key section 1 are nested together to form an arc-shaped support slide, and the troughs of the corrugated beam 3 slide on the arc-shaped support slide. The variable-length support rod 5 is a nested telescopic structure, hydraulically driven, and does not provide lateral support stiffness. The axial direction of the variable-length support rod 5 is variable when it extends, which is an existing design.

[0035] The deformable fuselage skin includes a deformable support frame, sliding scales 13, and S-shaped heat insulation plates 14; there are multiple sets of sliding scales 13, which are arranged side by side on the outside of the deformable support frame; the cross-section of the S-shaped heat insulation plate 14 is S-shaped; there are multiple S-shaped heat insulation plates 14, which are spaced apart between adjacent sliding scales 13, and adjacent sliding scales 13 are slidably fitted together; the deformable support frame is located inside the sliding scales 13 and the S-shaped heat insulation plate 14.

[0036] The outer surface formed by the crests of the corrugated beam 3 is connected to the deformable support frame; the corrugated beam 3 and the deformable support frame can deform synchronously.

[0037] Normal fuselage structure such as Figure 1 As shown in ①, when the shape and arc length of the arched beam change, the variable-height support column 4 and the variable-length support rod 5 will automatically change their height, thereby causing the sliding key section 2 and the sliding groove section 1 to slide relative to each other. At the same time, the corrugated beam 3 evenly distributes the change in arc length between adjacent crests, so that the external load is evenly distributed on the arched beam. This allows both the arched beam and the arc length to be changed, better adapting to the needs of structural shape changes, and the external load is evenly distributed on the arched beam. After the arc length of the corrugated beam changes, the deformable support frame transmits the change in arc length to the sliding scales and the S-shaped heat insulation plate. The deformable support frame has sufficient out-of-plane stiffness and in-plane deformation capacity. The sliding scales 13 have the ability to evenly distribute the in-plane deformation to the skin surface. The S-shaped heat insulation plate 14 ensures the sealing and heat insulation capacity of the skin surface. Thus, the skin can change its shape with the changes in the fuselage, thereby achieving a stable circumferential variable shape of the fuselage structure.

[0038] During the changes in fuselage structure, the fuselage configuration during cruise is as follows: Figure 1 As shown in ②, the fuselage configuration at takeoff is as follows Figure 1 As shown in ③.

[0039] Among them, the corrugated beam 3 is connected to the deformable support frame. When the arc length of the corrugated beam changes, it can drive the deformable support frame to open up and achieve uniform change.

[0040] The variable height support column 4 and the variable length support rod 5 can preferably be an actuator or an electric push rod. When the arch beam deforms outward, the sliding key section 2 and the sliding groove section 1 move away from each other; when the arch beam deforms inward, the sliding key section 2 and the sliding groove section 1 move closer to each other; thus, the arc length changes, so that the fuselage size decreases accordingly with fuel consumption.

[0041] Preferably, the variable height support column 4 and the variable length support rod 5 are hinged to both ends of the slide section 1; both the variable height support column 4 and the variable length support rod 5 can be height adjusted in the radial direction of the arc-shaped support slide.

[0042] The deformable support frame includes multiple elastic plates 15, which are arranged parallel to the fuselage axis and connected to each other. The length of each elastic plate 15 is equivalent to the distance between the fuselage frames. Each elastic plate 15 has a connecting plate 16 and a flexural plate staggered along its length. The upper edge of the connecting plate 16 is connected to the sliding scale 13. The two sides of the flexural plate are welded to the elastic plate 15. The S-shaped heat insulation plate 14 and the elastic plate 15 are both made of elastic material, which can be adjusted when the shape of the fuselage changes.

[0043] Through the above design, the deformable support frame can deform uniformly in accordance with the variable height support column 4 and the variable length support rod 5.

[0044] like Figures 4-6 Preferably, the flexural plate includes an upper flexural plate 17 and a lower flexural plate 18. The lower edge of the connecting plate 16 is on the same straight line as the lower edge of the lower flexural plate 18, and the upper edge of the connecting plate 16 is higher than the upper edge of the upper flexural plate 17. The upper edge of the connecting plate 16 is connected to the sliding scale 13. The upper flexural plate 17 and the lower flexural plate 18 have opposite flexural directions perpendicular to the plate surface; the flexural plates on the same level connected to both sides of the connecting plate 16 have opposite flexural directions. The flexural plates close to each other on the same level of adjacent elastic plates 15 are welded together to form a double-layer deformable support frame.

[0045] By setting up a double-layered flexure plate and connecting plate 16, the connection between the elastic plate 15 and the sliding scale 13 is ensured to have both high strength and stable deformation, thus ensuring the overall deformation stability of the skin.

[0046] Preferably, the flexural plates on adjacent elastic plates 15 are welded together, and the connecting plate 16 is integrally formed with the flexural plates on different layers to form a double-layer deformable support frame. This support frame evenly distributes the circumferential deformation of the fuselage to each elastic plate 15 and has sufficient out-of-plane support stiffness. This makes the connecting plate 16 both a component for connecting the flexural plates and a component for connecting the sliding scales 13 to the deformable support frame, resulting in a high structural utilization rate.

[0047] Preferably, it also includes reinforcing ribs, which are arranged in multiple sets and spaced apart along the circumference of the deformable fuselage frame. The flexural plate of the deformable support frame is welded to the adjacent reinforcing ribs, and the elastic plate 15 of the deformable support frame is connected to the crest of the corrugated beam 3 of the deformable fuselage frame, thereby strengthening the connection between the deformable fuselage frame and the skin.

[0048] Preferably, the sliding scale 13 includes a horizontal plate and a vertical plate. The horizontal plate is arranged along a direction perpendicular to the fuselage axis, and the vertical plate is integrally and vertically connected to the middle position of the horizontal plate. The cross-sections of the horizontal and vertical plates are T-shaped, and the cross-section of the horizontal plate is stepped. The upper layer of the horizontal plate slides into the lower layer of the horizontal plate within the adjacent sliding scale 13, and the lower layer of the horizontal plate slides into the upper layer of the horizontal plate of the adjacent sliding scale 13. In this way, when the fuselage shape changes, the deformation transmitted to the sliding scale 13 will be converted into relative sliding between adjacent sliding scales 13, thereby achieving stable deformation of the skin. The width of the horizontal edge must meet the requirements of the deformation amount.

[0049] Preferably, a slot is provided on the side wall of the vertical plate, and the upper edge of the connecting plate 16 is connected to the slot of the vertical plate; the end of the S-shaped heat insulation plate 14 is sealed to the side wall of the vertical plate to improve the connection stability.

[0050] Preferably, the S-shaped heat insulation plate 14 is made of a high-toughness heat insulation material. Both ends of the S-shaped heat insulation plate 14 are welded to the vertical plates of the adjacent sliding scales 13. The length of the S-shaped heat insulation plate 14 is the same as the length of the sliding scales 13, and the arc length of the S-shaped heat insulation plate 14 is greater than the maximum sliding distance between adjacent sliding scales 13. The heat insulation plate is made into an S-shaped structure to accommodate deformation, allowing the S-shaped heat insulation plate 14 to deform along with the sliding scales 13 while ensuring effective heat insulation performance.

[0051] like Figures 7-8 Preferably, the cross-section of the key section 2 is dovetail-shaped, and the middle of the groove section 1 is provided with a dovetail groove that mates with the key section 2; both the key section 2 and the groove section 1 have reinforcing ribs on their upper bottom surfaces to improve strength. The two sides of the dovetail are connected at the exact middle position along the length of the groove section 1. It is necessary to control the cross-sectional stiffness of the groove section 1 and the key section 2 so that a certain amount of elastic deformation can occur during the shape change of the arch beam, such as by using aluminum alloy, to ensure smooth sliding between the groove section 1 and the key section 2.

[0052] The corrugated beam 3 is formed by bending a long strip of metal plate. The crests and troughs of the corrugated beam 3 have similar structures, and its length is variable. The reinforcing ribs of the key section 2 and the groove section 1 are distributed in the middle and on both sides, respectively. The upper surfaces of the key section 2 and the groove section 1 are on the same plane, forming a support rail 6 that can slide with the corrugated beam 3. Support pulleys 7 are provided at the positions of the troughs of the corrugated beam 3 corresponding to the support rail 6. Each trough of the corrugated beam 3 slides on the support rail 6 through the support pulleys 7. The corrugated beam 3 evenly distributes the change in arc length of the arc-shaped support rail 6 to the arc surface formed by the crests. The arc length on the crest surface deforms uniformly, and the out-of-plane load of the variable arc length arched beam is evenly distributed on the arched beam.

[0053] like Figures 9-10 Preferably, the supporting pulley 7 includes a pulley seat 8 and sliding rollers 9. There are three sets of sliding rollers 9, each corresponding to a set of reinforcing ribs. Adjacent sliding rollers 9 are connected by axles 10. The middle sliding roller 9 is correspondingly positioned with the supporting slide rail 6 on the keyway section 2. The upper end of the pulley seat 8 is bolted to the corrugated beam 3, and the lower end is slidably engaged with the axle 10 of the sliding rollers 9. When the position of the corrugated beam 3 changes, the position of the pulley seat 8 changes, thereby driving the three sets of sliding rollers 9 to slide on the keyway section 2 and the groove section 1 via the axle 10, achieving a uniform change in arc length.

[0054] Preferably, the lower end of the pulley seat 8 is provided with a fork lug 11, and a notch is opened on the fork lug 11, which is connected to the wheel axle 10; and the length of the upper end of the pulley seat 8 is slightly greater than the width of the corrugated beam 3, and the width is slightly greater than the diameter of the sliding roller 9; the arc end face of the fork lug 11 has a certain gap with the upper surface of the sliding groove section 1 or the sliding key section 2, and is lower than the upper surface of the sliding groove section 1 and the sliding key section 2, so as to ensure smooth cooperation between the corrugated beam 3 and the sliding key section 2 and the sliding groove section 1.

[0055] Preferably, the arc-shaped support slide includes four sliding groove sections 1 and three sliding key sections 2. The length of the sliding groove section 1 is L, and the length of the sliding key section 2 is 1.5 times the length of the sliding groove section 1. Each sliding key section 2 is nested by two adjacent sliding groove sections 1 for 0.5L, and the length not nested in the sliding groove section 1 is 0.5L. When deformed to the maximum arc length, each sliding key section 2 slides out of the sliding groove section 1 by 0.3L, and the end of the sliding key section 2 overlaps with the sliding groove section 1 by 0.2L.

[0056] Two variable-height support columns 4 support one end of two sliding sections 1 nested within a middle sliding key section 2. The other ends of these two sliding sections 1 are supported by variable-length support rods 5. When the variable-height support columns 4 extend to their maximum length, the middle sliding key section 2 slides out 0.3L from each of the two sliding sections 1. The other two sliding sections 1 are supported at one end by variable-length support rods 5, and the other ends are fixed to the foundation structure. There are a total of 4 variable-length support rods 5. The length of the variable-length support rods 5 is adjusted so that the two ends of each sliding section 1 are on the contour line of the changing arch.

[0057] like Figure 11 Preferably, the variable height support column 4 includes a shell 19, a series of butterfly-shaped flexible devices 20, and a driving device 21; the shell 19 is a regular hexagon with a hollow internal structure and an open top; the series of butterfly-shaped flexible devices 20 and the driving device 21 are both located inside the shell 19; the series of butterfly-shaped flexible devices 20 includes multiple sets of vertically stacked flexible plates, each with a circular hole in its center, and the flexible plates are coaxially arranged with the shell 19; the driving device 21 is coaxially arranged with the shell 19, with its upper end extending from the top opening of the shell 19 and its middle part inserted into the center of the flexible plate; the shell 19 includes multiple sections of column 22, which are arranged vertically, with adjacent sections of column 22 nested and slidingly engaged.

[0058] When the height of the support column needs to be adjusted, the multi-section column 22 is driven up and down by the drive device 21. At the same time, the flexible plate expands or contracts under its own elastic force, thereby realizing the height adjustment of the support column. The structure is simple and the control is stable. Meanwhile, the variable height support column 4 has sufficient lateral stiffness to resist lateral loads and torque loads during the height change process, and the manufacturing process is simple and easy to implement. The drive device 21 uses a hydraulic actuator or an electric push rod to resist axial loads.

[0059] In a specific example, assuming the deformable fuselage structure is used in a hypersonic environment, the fuselage structure of the deformable part is as follows: Figure 1 As shown, the cruise configuration is approximately arc-shaped with a central angle of 70° and a radius R of 1.35 meters. The length L of a single slide segment 1 is 0.3 meters, and the length 1.5L of the slide key segment 2 is 0.45 meters. The deformable fuselage frame consists of four slide segments 1 and three slide key segments 2, with an arc length of 5.5L (1.65 meters). In the takeoff configuration, the slide segments 1 are raised to form a new arc shape. The highest point in the middle of the arc is 0.35 meters higher than in the cruise configuration. Each slide key segment 2 slides out 0.3L from each of the two adjacent slide segments 1, making the total arc length 7.3L (2.19 meters). The arc lengths in other intermediate states vary proportionally based on the length of the slide key segment 2 sliding out of the slide segment 1. Taking the structure between two adjacent deformable fuselage frames as an example, the frame spacing is 0.35 meters.

[0060] First press Figure 2 The basic fuselage structure of the deformable fuselage frame is arranged, with support points provided for the variable-length support rod 5 and the variable-height support column 4. Sufficient space must be provided to accommodate the deformation stroke of the variable-height support column 4 and the variable-length support rod 5. Then, a variable-arc length arc-shaped support slide is arranged. This arc-shaped support slide consists of four 0.3-meter-long sliding groove sections 1 and three 0.44-meter-long sliding key sections 2. In the cruise configuration, both ends of the sliding key sections 2 are nested within adjacent sliding groove sections 1 for 0.145 meters, with an unnested length of 0.15 meters. The arc-shaped support slide is 1.65 meters long.

[0061] The sliding key section 2 is 0.44 meters long and has a trapezoidal cross-section. The cross-sectional shape is as follows: Figure 5 The upper bottom is 15 mm wide, the lower bottom is 25 mm wide, and the height is 20 mm. The chute section 1 is 0.3 m long and matches the cross-section of the keyway section 2. Its bottom edge is 45 mm wide and 30 mm high, machined using sheet metal or profiles, and closed at the lower bottom edge. A 10 mm wide strip connects the two sides of the dovetail groove at the very center of the chute section 1 along its length (0.15 m from the end). The keyway section 2 has a slide height of 5 mm and a width of 10 mm, while the chute section 1 has a slide height of 5 mm and a width of 8 mm, positioned to match the sliding roller 9. The cross-sectional stiffness of the chute section 1 and keyway section 2 needs to be controlled to allow for a certain degree of elastic deformation during changes in the shape of the machine frame.

[0062] The corrugated beam 3 is made of a 2 mm thick and 15 mm wide steel strip, forming a continuous sine wave with a wave height of 15 mm and a wavelength of 20 mm, with a total length of 1.65 meters. The corrugated beam 3 slides on the support track via the support pulley 7. The support pulley 7 mainly includes a pulley seat 8 and a sliding roller 9 (see...). Figure 5 The sliding roller 9 has a diameter of 10 mm, a middle section roller length of 12 mm, two side rollers lengths of 9 mm, and two intermediate shafts with a diameter of 3 mm, machined from a 40 mm long and 10 mm diameter cylinder; the support pulley 7 has a length of 20 mm and a width of 13 mm, the fork lug 11 has a height of 12 mm from its axis to its upper end face, a 3 mm notch on the fork lug 11 that matches the shaft of the sliding roller 9, the fork lug 11 has a thickness of 3 mm, and the gap between the arc end face of the fork lug 11 and the upper surface of the slide groove section 1 (slide key section 2) is 3 mm; the corrugated beam 3 is connected to the pulley seat 8 with M3 screws.

[0063] Then follow Figure 2Variable-length support rods 5 and variable-height support columns 4 are arranged between the basic fuselage structure and the chute section 1 of the arc-shaped support slide. In this scheme, four variable-length support rods 5 are used. One end of the variable-length support rod 5 is hinged to one end of the chute section 1, and the other end is hinged at the corresponding position of the basic fuselage structure. The angles between the axis of the support rod and the line connecting the highest point of the arc center of the support slide to the center of the arc curvature are ±16.25° and ±22.75°, respectively. Two variable-height support columns 4 are used to support the two chute sections 1 nested with the middle sliding key section 2, respectively. One end of the support column is hinged to one end of the chute section 1, and the other end is fixed at the corresponding position of the basic fuselage structure. When the support column is raised along the axis to raise the arc-shaped support slide to the highest position (raised 0.35 meters), the middle sliding key section 2 slides out 0.3L (0.09 meters) from the adjacent chute section 1.

[0064] To ensure sufficient lateral and torsional stiffness of the variable-height support column, this design uses three nested regular hexagonal tubes as the sidewalls of the support column, with a wall thickness of 2 mm. The inner diameter of the inner circle of the uppermost section is 92 mm, and the end of the lowermost section is fixed to the foundation structure. A series of flexible disc-shaped devices are installed in the middle of the tube wall, and the drive device 21 passes through the central hole of the series of flexible disc-shaped devices. The flexible plate of the series of flexible disc-shaped devices is a 1.5 mm thick, 90 mm diameter circular aluminum plate. The diameter of the circular hole at the center of the flexible plate is 15 mm; the diameter of the middle circular plate is 40 mm. The outer edge of the plate is divided into 12 sector areas. The odd-numbered sector areas (shaded areas) and even-numbered sector areas bend in opposite directions on the plate surface. The spacing between adjacent flexible plates is 10 mm. The initial bending shape of the flexible plate is shown in [details omitted]. Figure 5 The outermost welding area is 3 mm wide. Adjacent flexible plates have adjacent fan-shaped areas welded together to form interlocking discs. The remaining reverse-bent fan-shaped areas are then welded to adjacent fan-shaped areas on the next adjacent flexible plate to form a series-connected disc-shaped flexible device. The drive device 21 passes through the circular hole in the middle of the flexible plate and is connected to the side wall of the support column at the upper end. The series-connected disc-shaped flexible device is easily deformed in the direction perpendicular to the flexible plate, but has high stiffness in all directions parallel to the flexible plate surface. The series-connected disc-shaped flexible device increases the ability of the variable-height support column 4 to resist lateral loads and torques.

[0065] Finally, a deformable fuselage skin with heat insulation function is installed. According to... Figure 7The elastic plates 15 arranged parallel to the fuselage axis are connected to each other to form a deformable support frame. The length of the elastic plate 15 is 0.35 meters (equivalent to the distance between the fuselage frames). It is made of 1.5 mm thick titanium alloy plate. Each elastic plate 15 has multiple sets of connecting plates 16 and flexural plates arranged alternately in the length direction. The connecting plate 16 is 10 mm long and the flexural plate is 30 mm long. The height of the flexural plate (i.e. the width of the elastic plate 15) is 16 mm. It is divided into two layers in the height direction. The lower edge of the connecting plate 16 and the lower edge of the lower flexural plate 18 are on the same straight line. The upper edge of the connecting plate 16 is 8 mm higher than the upper edge of the upper flexural plate 17. The upper flexural plate 17 and the lower flexural plate 18 flex in different directions perpendicular to the plate surface. The flexural plates before and after the connecting plate 16 on the same layer flex in different directions. The initial flexural shape is made with a spacing of 10 mm between the elastic plates 15. Figure 5 The solid lines represent the upper layer of the flexible mesh, and the dashed lines represent the lower layer. Then, the flexible plates on the same layer of adjacent elastic plates 15 that are close to each other are welded together. The connecting plate 16 connects the flexible meshes of the two layers together, forming a double-layer deformable support frame (see...). Figure 6 Adaptive treatment is required at the ends of the deformable support frame so that the deformable fuselage frame can be connected to the corrugated beam 3, and the upper edge of the upper flexural plate 17 is approximately equal to the height of the crest of the corrugated beam 3.

[0066] The sliding scale 13 is made of 1 mm thick titanium alloy plate, 350 mm long, with a T-shaped cross section, 20 mm high vertical side, 15 mm wide horizontal side on each side, arranged parallel to the fuselage axis, and 20 mm apart between adjacent vertical sides.

[0067] Finally, it should be noted that the accompanying drawings of the embodiments disclosed in this invention only involve the structures involved in the embodiments disclosed in this invention. Other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of this invention can be combined with each other.

[0068] In conclusion, the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A morphing fuselage structure for a hypersonic environment, characterized by: The fuselage includes a deformable frame and a deformable skin. The deformable frame includes a slide section (1), a slide key section (2), a corrugated beam (3), a variable height support column (4), and a variable length support rod (5). The corrugated beam (3) is located outside the slide key section (2) and the slide section (1), and the corrugated beam (3) has a peak and a trough structure. The slide key section (2) and the slide key section (1) are located inside the corrugated beam (3) and are spaced apart. The slide key section (2) and the slide key section (1) are staggered. The corrugated beam (3), the slide key section (2), and the slide key section (1) are all arc-shaped structures. The peaks and troughs of the corrugated beam (3) are arranged along the radial direction of the arc-shaped structure. The slide key section (2) and the slide key section (1) are nested together to form an arc-shaped support slide. The troughs of the corrugated beam (3) slide on the arc-shaped support slide. The deformable fuselage skin includes a deformable support frame, sliding scales (13), and an S-shaped heat insulation plate (14); there are multiple sets of sliding scales (13), which are arranged side by side on the outside of the deformable support frame; the cross-section of the S-shaped heat insulation plate (14) is S-shaped; there are multiple S-shaped heat insulation plates (14) and they are spaced apart between adjacent sliding scales (13), and adjacent sliding scales (13) are slidably fitted together; the deformable support frame is located inside the sliding scales (13) and the S-shaped heat insulation plate (14); The outer surface formed by the crest of the corrugated beam (3) is connected to the deformable support frame; the corrugated beam (3) and the deformable support frame can deform synchronously.

2. The deformable fuselage structure for hypersonic environments as described in claim 1, characterized in that: The variable height support column (4) and the variable length support rod (5) are respectively hinged to both ends of the slide section (1); the variable height support column (4) and the variable length support rod (5) can both be height adjusted, and the adjustment direction is the radial direction of the arc-shaped support slide. The deformable support frame includes multiple elastic plates (15), which are arranged parallel to the fuselage axis and connected to each other. The length of the elastic plates (15) is equivalent to the distance between the fuselage frames. Each elastic plate (15) is staggered with a connecting plate (16) and a flexural plate in the length direction. The upper edge of the connecting plate (16) is connected to the sliding scale (13). The S-shaped heat insulation plate (14) and the elastic plate (15) are both made of elastic material. When the shape of the fuselage changes, the sliding scales (13) and the S-shaped heat insulation plate (14) can deform uniformly with the elastic plate (15).

3. The deformable fuselage structure for hypersonic environments as described in claim 2, characterized in that: The flexural plate includes an upper flexural plate (17) and a lower flexural plate (18). The lower edge of the connecting plate (16) is on the same straight line as the lower edge of the lower flexural plate (18). The upper edge of the connecting plate (16) is higher than the upper edge of the upper flexural plate (17). The upper edge of the connecting plate (16) is connected to the sliding scale (13). The upper flexural plate (17) and the lower flexural plate (18) have opposite flexural directions on the vertical plate surface. The flexural plates on the same level that are connected to both sides of the connecting plate (16) have opposite flexural directions.

4. The deformable fuselage structure for hypersonic environments as described in claim 3, characterized in that: The flexible plates on adjacent elastic plates (15) are welded together, and the connecting plate (16) is integrally formed with the flexible plates on different layers to form a double-layer deformable support frame.

5. The deformable fuselage structure for hypersonic environments as described in claim 3, characterized in that: It also includes reinforcing ribs, which are arranged in multiple sets and spaced apart along the circumference of the deformable fuselage frame. The flexural plate of the deformable support frame is welded to the adjacent reinforcing ribs, and the elastic plate (15) of the deformable support frame is connected to the crest of the corrugated beam (3) of the deformable fuselage frame.

6. The deformable fuselage structure for hypersonic environments as described in claim 1, characterized in that: The sliding scale (13) includes a horizontal plate and a vertical plate. The horizontal plate is arranged along a direction perpendicular to the fuselage axis. The vertical plate is integrally and vertically connected to the middle position of the horizontal plate. The cross-section of the horizontal plate and the vertical plate is T-shaped, and the cross-section of the horizontal plate is stepped. The upper layer of the horizontal plate slides in conjunction with the lower layer of the horizontal plate in the adjacent sliding scale (13), and the lower layer of the horizontal plate slides in conjunction with the upper layer of the horizontal plate in the adjacent sliding scale (13).

7. The deformable fuselage structure for hypersonic environments as described in claim 2, characterized in that: The cross-section of the sliding key section (2) is dovetail-shaped, and the middle part of the sliding groove section (1) is provided with a dovetail groove that matches the sliding key section (2); both the upper bottom surfaces of the sliding key section (2) and the sliding groove section (1) are provided with reinforcing ribs.

8. The deformable fuselage structure for hypersonic environments as described in claim 7, characterized in that: The reinforcing ribs of the key section (2) and the groove section (1) are distributed in the middle and on both sides respectively. The upper bottom surfaces of the key section (2) and the groove section (1) are on the same plane, forming a support slide rail (6) that can slide with the corrugated beam (3). The troughs of the corrugated beam (3) are provided with support pulleys (7) at the positions corresponding to the support slide rail (6). Each trough of the corrugated beam (3) slides on the support slide rail (6) through the support pulleys (7).

9. The deformable fuselage structure for hypersonic environments as described in claim 8, characterized in that: The supporting pulley (7) includes a pulley seat (8) and a sliding roller (9). There are three sets of sliding rollers (9) and three sets of reinforcing ribs respectively. A wheel axle (10) connects adjacent sliding rollers (9). The middle sliding roller (9) is correspondingly set with the supporting slide rail (6) on the keyway section (2). The upper end of the pulley seat (8) is bolted to the corrugated beam (3), and the lower end is slidably engaged with the wheel axle (10) of the sliding roller (9).

10. The deformable fuselage structure for hypersonic environments as described in claim 2, characterized in that: The variable height support column (4) includes a shell (19), a series of butterfly-shaped flexible devices (20), and a drive device (21). The shell (19) is a regular hexagon with a hollow structure inside and an open top. The series of butterfly-shaped flexible devices (20) and the drive device (21) are both located inside the shell (19). The series of butterfly-shaped flexible devices (20) includes multiple sets of flexible plates stacked vertically. A circular hole is opened in the center of the flexible plate. The flexible plate is coaxially arranged with the shell (19). The drive device (21) is coaxially arranged with the shell (19). The upper end of the drive device (21) extends from the top opening of the shell (19) and is inserted into the center of the flexible plate. The shell (19) includes multiple sections of column (22). The multiple sections of column (22) are arranged vertically, and adjacent sections of column (22) are nested and slidably fitted together.

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