A flexible variable configuration device for a carrier

Abstract

The invention discloses a carrier flexible variable configuration device, comprising a fuselage, characterized in that it also comprises: an inflatable nose cone, an inflatable glider and a plurality of inflatable devices; the inflatable nose cone is placed at the head of the fuselage, and the inflatable glider is placed on both sides of the fuselage near the tail; the inflatable nose cone comprises a rigid heat-proof nose cone, a support airbag and an airbag cabin; the support airbag is inflated by the inflatable device connected to the airbag cabin, and the rigid heat-proof nose cone is supported along the axial direction to realize the axial expansion of the inflatable nose cone. The invention has high structural rigidity and high expansion accuracy, and meets the heat protection and load-bearing requirements under high heat flux density and large-scale aerodynamic loads.

Description

Technical Field

[0001] The invention relates to a carrier flexible variable configuration device, belonging to the technical field of carrier structures. Background Art

[0002] At present, vertical take-off and landing vehicles are one of the important technical ways to reduce the cost of vehicles. The research on vertical take-off and landing vehicles at home and abroad is mainly focused on the "bottom reentry" method of Falcon9 rockets. The vertical take-off and landing rocket schemes based on different power sources proposed by them all adopt the rocket "bottom reentry" return. At present, there is little research on the "head reentry" return technology at home and abroad. The research related to the use of flexible variable configuration to complete the "head reentry" return is currently in a blank stage at home and abroad. In this patent, a head reentry vertical landing method is proposed. The first stage of the vertical take-off and landing vehicle has an axisymmetric shape during the ascent process. After the first and second stages are separated, a flexible variable configuration is used, the nose cone is inflated and unfolded, and the glider is inflated and unfolded. The first stage is transformed into a winged aircraft with a certain lift-to-drag ratio, and returns by a head reentry method with a large angle of attack.

[0003] Since the flexible variable configuration such as inflatable structure was proposed, it has attracted the research of scholars from all over the world due to its light structure and simple inflation device. Inflatable flexible structure can be applied to aircraft wings, glider wings, inflatable space capsules, inflatable reentry reducers and other fields. This patent is based on the overall requirements of the carrier, and aims at the aerodynamic thermal protection of reentry, the folding and reliable deployment of flexible structure, the bearing and stiffness maintenance of atmospheric dynamic loads, etc., and conducts research from the aspects of structural scheme design and bearing capacity. It includes flexible material scheme, folding scheme, inflation deployment scheme, flexible structure scheme, and inflation pressure design; conduct simulation analysis to obtain the deformation of flexible structure under different flight conditions, and provide a technical basis for exploring new routes for rocket sub-stage recovery. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art and to provide a carrier flexible variable configuration device with high structural rigidity and high deployment accuracy, which can meet the heat protection and load-bearing requirements under high heat flux density and a large number of aerodynamic loads.

[0005] The technical solution of the present invention is:

[0006] The present invention discloses a flexible variable configuration device for a carrier, comprising a fuselage, and also comprising: an inflatable nose cone, an inflatable hang glider and a plurality of inflatable devices; the inflatable nose cone is arranged at the head of the fuselage, and the inflatable hang glider is arranged on both sides of the fuselage near the tail; the inflatable nose cone comprises a rigid heat-proof nose cone, a supporting airbag and an airbag cabin; the supporting airbag is inflated by the inflatable device connected to the airbag cabin, and the rigid heat-proof nose cone is supported along the axial direction, so as to realize the axial expansion of the inflatable nose cone.

[0007] In the above device, the inflatable nose cone also includes a flexible heat-proof skin, which is located on the outside of the inflatable nose cone and is made of heat-proof material.

[0008] In the above device, the inflatable nose cone is a single-cavity support structure. When the inflatable nose cone is in an inflated and expanded state, the cross-sectional shape of the single-cavity support structure along the axial direction is a parabola.

[0009] In the above device, the inflatable device includes a first inflatable device and a second inflatable device, the first inflatable device is located in the inflatable nose cone, and the second inflatable device is located in the glider.

[0010] In the above device, the first inflation device and the second inflation device both include an inflation bottle and a timed inflation valve connected to the inflation bottle, and the timed inflation valve opens the valve at a fixed time by timing to control the inflation bottle to inflate.

[0011] In the above device, the inflatable hang glider includes a rigid ablation-resistant structure, a plurality of support hinges, support ribs, a flexible heat-insulating structure, a fixed shaft and fixed ribs;

[0012] Wherein, the supporting hinge comprises a plurality of hinges connected in series, each hinge comprising a chain and a rotating shaft;

[0013] The supporting ribs are composed of a number of ribs which gradually increase from the inside to the outside, one end of each rib is connected to the rotating shaft; the number of the ribs matches the number of the rotating shafts; the other end of each rib is mechanically connected to the fixed rib.

[0014] The flexible thermal insulation structure covers the outer side of the supporting ribs;

[0015] The rigid ablation-resistant structure is arranged at the leading edge of the inflatable hang glider and is mechanically connected to the supporting ribs at the leading edge of the inflatable hang glider.

[0016] The fixed axis is located outside the smallest rib among the supporting ribs, and the supporting ribs are rotated and unfolded around the fixed axis; the rigid ablation-resistant structure and the supporting ribs are rotated and folded around the fixed axis to achieve the overall folding and folding of the inflatable hang glider.

[0017] In the above device, the inflatable hang glider further comprises a supporting rib, and the ends of the supporting rib, the ends of the fixed rib and the ends of the fixed shaft are fixedly connected in pairs to form a triangular structure.

[0018] In the above device, when the inflatable glider is unfolded, the rigid ablation-resistant structure is rotated around the fixed axis of the leading edge by inflating the interior of the glider structure, while pulling the tail support hinge and the flexible insulation structure to unfold step by step, ultimately achieving the overall unfolding of the glider structure and maintaining its rigidity.

[0019] In the above device, the rigid heat-proof nose cone comprises, from the outside to the inside, an ablation-resistant material layer, a heat-insulating material layer and a supporting and connecting structure layer.

[0020] In the above device, the flexible heat-proof skin is composed of multiple layers of flexible heat-insulating material.

[0021] In the above device, the maximum diameter of the inflatable nose cone after unfolding is 2-5m, and the height is 3-5m; the maximum thickness of the inflatable glider after unfolding is 0.5-2m, the minimum thickness is 0.3-1m, the chord length is 5-10m, and the wingspan is 3-5m.

[0022] In the above device, the inflatable nose cone and the inflatable hang glider are seamlessly connected or integrally formed with the fuselage by means of a smooth transition.

[0023] The beneficial effects of the present invention and the prior art are:

[0024] (1) The present invention innovatively adopts an inflatable and deployable structure variable configuration scheme in the design of the first stage structure of the vertical take-off and landing vehicle. The nose cone and wings of the vehicle are in a folded state during the ascending flight. During the reentry process, the nose cone is inflated and deployed into a streamlined configuration, and the wings are inflated and deployed into a nearly trapezoidal configuration. This is beneficial to the deceleration and control of the first stage.

[0025] (2) The inflatable nose cone of the present invention adopts a single-cavity support structure with high structural rigidity, relatively simple internal structure, and high deployment accuracy, which can meet the heat protection and load-bearing requirements under high heat flux density and large-scale aerodynamic loads.

[0026] (3) The flexible inflatable wing designed in the present invention adopts a lightweight structure of multi-cavity intersecting load-bearing plates connected to circular tubes. The deformation amount during aerodynamic deceleration is small, and the flexible inflatable wing has a strong ability to maintain its shape under large-scale aerodynamic loads.

[0027] (4) The flexible inflatable wing designed by the present invention can reduce weight by 25% compared with a rigid wing. The technology related to the flexible inflatable deformation structure can be applied to aerodynamic deceleration or landing cushioning of other aircraft, and has broad application prospects. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a schematic diagram of the overall layout of the inflatable structure of the vehicle of the present invention in the folded state and the unfolded state; Figure 1 (a) is a schematic diagram of the inflatable structure in a collapsed state. Figure 1 (b) is a schematic diagram of the inflatable structure in the unfolded state;

[0029] Figure 2 This is the inflatable head cone single cavity support structure solution of the present invention;

[0030] Figure 3 It is a schematic diagram of the inflatable nose cone of the present invention being inflated and deployed;

[0031] Figure 4 This is the inflatable wing multi-cavity intersecting bearing plate connected circular tube structure solution of the present invention;

[0032] Figure 5 The inflatable wing of the present invention is shown in FIG. Figure 5 (a) is a schematic diagram of the folded state of the inflatable wing. Figure 5 (b) is a schematic diagram of the inflatable wing in a semi-expanded state; Figure 5 (c) is a schematic diagram of the fully expanded state of the inflatable wing;

[0033] Figure 6 It is a schematic diagram of the support hinge of the present invention. DETAILED DESCRIPTION

[0034] The present invention is further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0035] like Figure 1 to Figure 5 As shown, the present invention provides a flexible variable configuration device for a carrier, comprising a fuselage, an inflatable nose cone 1, an inflatable hang glider 2 and a plurality of inflatable devices; the inflatable nose cone 1 is placed at the head of the fuselage, and the inflatable hang glider 2 is placed on both sides of the fuselage near the tail; the inflatable nose cone 1 comprises a rigid heat-proof nose cone 3, a supporting airbag 4 and an airbag cabin 6; the inflatable device connected to the airbag cabin 6 inflates the supporting airbag 4, supports the rigid heat-proof nose cone 3 along the axial direction, and realizes the axial expansion of the inflatable nose cone 1.

[0036] The inflatable nose cone also includes a flexible heat-proof skin 5, which is located on the outside of the inflatable nose cone 1 and is made of heat-proof material. The inflatable nose cone 1 is a single-cavity support structure. When the inflatable nose cone 1 is in an inflated and expanded state, the cross-sectional shape of the single-cavity support structure along the axial direction is a parabola. The inflatable device includes a first inflatable device 11 and a second inflatable device 12. The first inflatable device 11 is located in the inflatable nose cone 1, and the second inflatable device 12 is located in the hang glider 2. The first inflatable device 11 and the second inflatable device 12 both include an inflatable bottle and a timed inflating valve connected to the inflatable bottle. The timed inflating valve opens the valve at a fixed time by timing to control the inflatable bottle to inflate.

[0037] The inflatable hang glider 2 includes a rigid ablation-resistant structure 7, a plurality of support hinges 8, support ribs 9, a flexible heat-insulating structure 10, a fixed shaft 13 and a fixed rib 14; wherein the support hinge 8 includes a plurality of chains 81 and a rotating shaft 82; the support rib 9 is composed of a plurality of ribs that gradually increase in size from the inside to the outside, and one end of each rib is connected to the rotating shaft 82; the number of ribs matches the number of rotating shafts 82; the other end of each rib is mechanically connected to the fixed rib 14. The inflatable hang glider 2 also includes support ribs 15, and the ends of the support ribs 15, the ends of the fixed ribs 14 and the ends of the fixed shaft 13 are fixedly connected in pairs to form a triangular structure. Figure 6As shown in the figure, the flexible heat-insulating structure 10 covers the outer side of the supporting rib 9; the rigid ablation-resistant structure 7 is placed at the leading edge of the inflatable hang glider and mechanically connected to the supporting rib 9 at the leading edge of the inflatable hang glider. The fixed axis 13 is located outside the smallest rib among the supporting ribs 9, and the supporting ribs 9 are rotated and unfolded around the fixed axis 13; the rigid ablation-resistant structure 7 and the supporting ribs 9 are rotated and folded around the fixed axis 13 to realize the overall folding and folding of the inflatable hang glider.

[0038] When the inflatable hang glider is unfolded, the rigid ablation-resistant structure 7 is rotated around the leading edge fixed axis 13 by inflating the inside of the hang glider structure, and the tail support hinge 8 and the flexible thermal insulation structure 10 are pulled to unfold step by step, and finally the overall unfolding of the hang glider structure is achieved while maintaining the rigidity. The rigid heat-resistant nose cone is composed of ablation-resistant material layer, thermal insulation material layer and support connection structure layer from the outside to the inside. The flexible heat-resistant skin is composed of multiple layers of flexible thermal insulation material.

[0039] After the inflatable nose cone is unfolded, the maximum diameter is 2 to 5 meters and the height is 3 to 5 meters; after the inflatable hang glider is unfolded, the maximum thickness is 0.5 to 2 meters and the minimum thickness is 0.3 to 1 meter, the chord length is 5 to 10 meters, and the wingspan is 3 to 5 meters. The inflatable nose cone 1 and the inflatable hang glider 2 are seamlessly connected or integrated with the fuselage by a smooth transition method.

[0040] Example 1

[0041] In this embodiment, the Mach number of the carrier during re-entry is relatively high, the inflatable wing is responsible for aerodynamic deceleration and providing lift, the re-entry aerodynamic load is large, and the thermal environment is harsh.

[0042] From the aerodynamic and thermal characteristics of the inflatable wing and the inflatable nose cone, it can be seen that the leading edge heat flux density is large, the temperature is high, and the dynamic pressure is large when the inflatable wing and the inflatable nose cone are working. It is difficult to achieve thermodynamic protection for the structure with commonly used flexible thermal insulation materials. Therefore, rigid thermal insulation materials with high stiffness and good temperature resistance can be selected for the leading edge of the inflatable wing and the top of the inflatable nose cone; the heat flux density of the upper and lower surfaces of the inflatable wing, the trailing edge of the wing, and other parts of the inflatable nose cone is slightly lower, and flexible thermal insulation materials can be selected to achieve the folding and gathering requirements of the structure while meeting the structural insulation requirements.

[0043] From the aerodynamic characteristics of the inflatable wing, it can be seen that the wing structure will provide a certain resistance to the rocket sub-stage structure under the action of the windward resistance area, and will also provide a certain lift to the rocket sub-stage under the influence of the structural configuration characteristics. It is also worth noting that since the inflatable wing structure is a flat structure with a long chord and a wide wingspan, and the carrier is heavy, the effect of the incoming flow resistance on the structural compression deformation is much lower than the effect of the lift on the structural bending. Therefore, in the structural design, the focus should be on the design of the structural cross-section to improve the overall bending resistance of the structure, thereby meeting the aerodynamic characteristics of the inflatable wing structure when it is working.

[0044] During the ascending flight phase, the inflatable nose cone is folded inside the head stage; the inflatable wings are folded inside the protective cover outside the box stage. The inflatable nose cone and the inflatable wings will not produce large protrusions when they are folded, so they will not produce large aerodynamic resistance. Figure 1 shown.

[0045] During the reentry phase, the inflatable nose cone and inflatable wings are in the unfolded state. Figure 1 To ensure that the vehicle has a strong deceleration capability during the "head reentry" return process, the inflatable nose cone adopts a streamlined configuration after being inflated by a high-pressure gas cylinder. It is located at the "head" of the vehicle and is mainly responsible for providing lift, deceleration and heat protection. After the inflatable wing receives the deceleration command, the high-pressure gas cylinder inflates the inflatable wing and pops open the protective cover. The inflated wing is symmetrically distributed in two approximately trapezoidal configurations, which are mainly responsible for deceleration and auxiliary heat protection.

[0046] In the reentry gliding deceleration stage of the vehicle in this embodiment, a flexible inflatable nose cone is deployed at the head of the vehicle, and a flexible inflatable wing is deployed at the middle of the body. The inflatable nose cone can shape the blunt body on the windward side, improve the flow characteristics of the head, and reduce the wall heat flow and stagnation temperature in the high-heat area of ​​the head; the inflatable wing can greatly improve the lift-to-drag ratio of the first stage, extend the hovering gliding time, and be more conducive to the deceleration and control of the first stage. It has a wide longitudinal and lateral adjustment capability, has a strong adaptability to the landing area, and is helpful for the vertical take-off and landing vehicle to return to the launch site.

[0047] (1) Inflatable head cone rigid heat protection material and heat protection design

[0048] The peak heat flux in the stagnation area of ​​the inflatable nose cone is hundreds of kilowatts per square meter, the heating lasts for tens of seconds, and the maximum temperature is thousands of degrees Celsius. According to the heat flux and temperature data of the stagnation area of ​​the inflatable nose cone, the rigid heat protection structure of the inflatable nose cone is designed as three layers. The first layer uses millimeter-level rigid non-ablative insulation tile heat protection material made of sintered quartz fiber as the ablation-resistant material, millimeter-level alumina insulation felt as the insulation material, and millimeter-level titanium alloy skeleton as the supporting connection structure, which can meet the thermal protection needs near the stagnation point of the inflatable nose cone.

[0049] (2) Inflatable head cone flexible heat protection material and heat protection design

[0050] The peak heat flux of the flexible part of the inflatable nose cone is hundreds of kilowatts per square meter, the heating duration is tens of seconds, and the maximum temperature is thousands of degrees Celsius. According to the heat flux distribution on the surface of the inflatable nose cone, multi-layer flexible insulation materials are selected to provide thermodynamic protection for the rigid-flexible junction and the flexible part of the inflatable nose cone. The overall thickness is in the millimeter level.

[0051] (3) Rigid heat-resistant materials and heat-resistant design of inflatable hang gliders

[0052] The peak heat flux in the stagnation line area on the windward side of an inflatable hang glider is hundreds of kilowatts per square meter, the heating lasts for tens of seconds, and the maximum temperature is over a thousand degrees Celsius, which is similar to the thermal environment of the stagnation area of ​​the inflatable nose cone. Therefore, the same rigid heat-proof material as that of the inflatable nose cone is used to achieve thermal protection for the inflatable hang glider structure.

[0053] (4) Flexible heat-resistant materials and heat-resistant design of inflatable hang gliders

[0054] The peak heat flux in the interference zone of the inflatable hang glider and the large area of ​​the glider wing is tens of kilowatts per square meter, the heating duration is tens of seconds, and the maximum temperature is hundreds of degrees Celsius. The heat flux in this area is small and the surface temperature is low. Therefore, a multi-layer insulation layer composed of an ablation-resistant layer, a silica aerogel insulation felt and a bearing layer can be used to achieve thermodynamic protection for the flexible structure of the inflatable hang glider. The overall thickness is in the millimeter level.

[0055] (5) Design of the inflatable nose cone deployment structure

[0056] The inflatable nose cone is designed as a single-cavity support structure scheme, an improved scheme proposed for the situation where the stagnation point dynamic pressure is much higher than other areas. The difference from the single-cavity structure scheme is that this scheme uses a supporting airbag to support the rigid heat protection nose cone along the axial direction, which not only ensures the support effect of the structure in the axial direction, but also greatly reduces the inflation volume of the structure. Before the structure works, the rigid heat protection nose cone, the flexible heat protection skin and the multi-cavity intersecting circular tubes are fixed in the airbag cabin in a folded and packaged state. When working, the multi-cavity intersecting circular tubes are inflated by the inflation device connected to the airbag cabin and unfolded to the designed shape. This scheme has a medium structure, medium folding difficulty, high structural rigidity, relatively simple internal structure, high unfolding accuracy, and strong bearing capacity.

[0057] (6) Inflatable nose cone structure folding and unfolding scheme

[0058] The center of the inflatable nose cone structure is a spherical crown-shaped rigid heat-protection structure, and the surrounding areas are flexible structures. At the same time, the inflatable nose cone is located in the cavity area between sub-stages, which requires that the folding of the inflatable nose cone is mainly axial folding. Therefore, the folding scheme of the inflatable nose cone adopts a method of horizontal movement of the rigid structure along the axial direction and radial Z-shaped folding of the flexible structure, which not only meets the requirements of the structural deployment form, but also enables the flexible structure to achieve axial folding without changing the diameter.

[0059] Inflatable head cone folding form Figure 3 As shown, in the folded state, the rigid nose cone is located at the center of the folded space, and the skin material is located outside the nose cone; the skin structure presents a sinusoidal curve with ups and downs from the center to the outside, and the axial positions in the folded and unfolded states correspond to each other. When unfolding, the nose cone structure is inflated inside so that the structure is inflated and unfolded along the axial direction under the action of the internal inflation pressure.

[0060] After the inflatable nose cone is folded in the above manner, the diameter of the folded area is slightly smaller than the diameter of the rocket, and the height of the folded area is the same as the height of the rigid heat-protective nose cone part.

[0061] (7) Design of the deployment structure of the inflatable hang glider

[0062] The rocket sub-stage is heavy, and the aerodynamic lift required by the glider during deceleration is large, which places high demands on the structural stiffness. Therefore, in order to improve the bending resistance of the structure, a multi-cavity bearing plate structure can be added to the pure inflatable tube structure solution, such as Figure 4 As shown in the figure, the direction of each bearing plate structure is consistent with the rigid heat protection structure, and a rotation axis is left at the front end of the structure. When the structure is inflated and expanded, each bearing plate and the rigid heat protection structure rotate along the rotation axis under the action of the pneumatic internal pressure, and at the same time drive the flexible heat insulation material to expand; after a certain pressure difference is established inside and outside the structure, each bearing plate and the rigid heat protection material rotate into place and ensure the position is fixed under the action of the inflatable cavity.

[0063] The scheme of connecting circular tubes with multi-cavity intersecting bearing plates adds intersecting partition bearing plates. Through the design of the bearing plate structure, the aerodynamic lift borne by the glider structure can be transmitted to the front end of the bearing plate, thereby greatly improving the bending resistance of the structure. However, the main flow direction of the airflow is the chord direction, the airflow movement distance is long, the inflation and deployment speed is slightly reduced, and the bearing plate is a metal plate or a composite material plate, which will increase the structural mass. In addition, since the airbag cavity is an intersecting circular tube structure, in order to ensure that the airbag structure is evenly stressed, the ratio of the protruding height of the airbag to its width is a constant value, and the width of the airbag is required to change continuously along the chord direction.

[0064] (8) Inflatable hang glider structure folding and unfolding scheme

[0065] The inflatable hang glider structure consists of a leading edge rigid heat protection structure, a tail support hinge structure, a flexible airbag structure, a support rib structure and a flexible insulation skin. The leading edge rigid heat protection and the support rib structure both rotate around the front fixed axis. Therefore, the folding of the inflatable hang glider structure adopts the rigid structure to rotate and retract along the fixed axis, and the flexible structure is evenly distributed on the upper and lower sides of the rigid structure to achieve the overall folding and retraction of the inflatable hang glider. The folding form of the inflatable hang glider structure is as follows: Figure 5As shown, when the inflatable glider is unfolded, the rigid ablative material rotates around the front rotation axis by inflating the inside of the glider structure, and at the same time, the tail support hinge structure and the flexible airbag structure are pulled to unfold step by step, and finally the overall unfolding of the glider structure is achieved while maintaining rigidity. Six connection and separation points are set outside the fixed cavity of the inflatable glider structure, which are six separation nuts for connection, fixation, unlocking and separation of the inflatable glider structure. A pipe cutter is left at the connection between the inflatable pipe and the inflatable glider. The pipe cutter and the separation nut are powered in turn according to the rocket body command to achieve the separation of the glider structure from the rocket sub-stage structure.

[0066] Although the content of the present invention has been described in detail through the above preferred embodiments, it should be appreciated that the above description should not be considered as a limitation of the present invention. After reading the above content, it will be apparent to those skilled in the art that various modifications and substitutions of the present invention will occur. Therefore, the protection scope of the present invention should be limited by the appended claims.

[0067] The contents not described in detail in the specification of the present invention belong to the common knowledge of the professionals in this field.

Claims

1. A carrier flexible configuration device, comprising a fuselage, characterized in that: Also includes: An inflatable nose cone (1), an inflatable hang glider (2) and a plurality of inflatable devices; the inflatable nose cone (1) is placed at the head of a fuselage, and the inflatable hang glider (2) is placed on both sides of the fuselage near the tail; the inflatable nose cone (1) comprises a rigid heat-resistant nose cone (3), a support airbag (4) and an airbag cabin (6); the support airbag (4) is inflated by an inflatable device connected to the airbag cabin (6), and the rigid heat-resistant nose cone (3) is supported along the axial direction to achieve axial expansion of the inflatable nose cone (1); the inflatable nose cone (1) is a single-cavity support structure, and when the inflatable nose cone (1) is in an inflated state, the cross-sectional shape of the single-cavity support structure along the axial direction is a parabola; The inflatable hang glider (2) comprises a rigid ablation-resistant structure (7), a plurality of support hinges (8), a first support rib (9), a flexible heat-insulating structure (10), a fixed shaft (13) and a fixed rib (14); Wherein, the support hinge (8) comprises a plurality of hinges connected in series, and each hinge comprises a chain (81) and a rotating shaft (82); The first supporting rib (9) is composed of a plurality of ribs which gradually increase in size from the inside to the outside, one end of each rib being connected to the rotating shaft (82); the number of ribs matches the number of rotating shafts (82); the other end of each rib is mechanically connected to the fixed rib (14); The flexible heat insulation structure (10) covers the outer side surface of the first supporting rib (9); The rigid ablation-resistant structure (7) is disposed at the leading edge of the inflatable hang glider and is mechanically connected to the first supporting rib (9) at the leading edge of the inflatable hang glider; The fixed axis (13) is located outside the smallest rib in the first supporting ribs (9), and the first supporting ribs (9) are rotated and unfolded around the fixed axis (13); the rigid ablation-resistant structure (7) and the first supporting ribs (9) are rotated and folded around the fixed axis (13), thereby realizing the overall folding and folding of the inflatable hang glider.

2. A carrier flexible configuration device according to claim 1, characterized in that: The inflatable nose cone also includes a flexible heat-proof skin (5), which is located on the outside of the inflatable nose cone (1) and is made of heat-proof material.

3. The carrier flexible configuration device according to claim 1, characterized in that: The inflatable device comprises a first inflatable device (11) and a second inflatable device (12); the first inflatable device (11) is located in the inflatable nose cone (1), and the second inflatable device (12) is located in the inflatable hang glider (2).

4. The carrier flexible configuration device according to claim 3, characterized in that: The first inflation device (11) and the second inflation device (12) both comprise an inflation bottle and a timed inflation valve connected to the inflation bottle, wherein the timed inflation valve opens the valve at a fixed time in a timing manner to control the inflation bottle to inflate.

5. The carrier flexible configuration device according to claim 1, characterized in that: The inflatable hang glider (2) also includes a second supporting rib (15), and the ends of the second supporting rib (15), the ends of the fixed rib (14) and the ends of the fixed shaft (13) are fixedly connected in pairs to form a triangular structure.

6. The carrier flexible configuration device according to claim 1, characterized in that: When the inflatable hang glider is unfolded, the inflatable hang glider structure is inflated to rotate the rigid ablation-resistant structure (7) around the leading edge fixed axis (13), and at the same time, the tail support hinge (8) and the flexible heat insulation structure (10) are pulled to unfold step by step, and finally the inflatable hang glider structure is unfolded as a whole and the rigidity is maintained.

7. The carrier flexible configuration device according to claim 1, characterized in that: The rigid heat-proof head cone (3) comprises, from the outside to the inside, an ablation-resistant material layer, a heat-insulating material layer and a supporting connection structure layer.

8. The carrier flexible configuration device according to claim 2, characterized in that: The flexible heat-proof skin (5) is composed of multiple layers of flexible heat-insulating material.

9. The carrier flexible configuration device according to claim 1, characterized in that: The inflatable nose cone (1) has a maximum diameter of 2 to 5 m and a height of 3 to 5 m after unfolding; the inflatable hang glider (2) has a maximum thickness of 0.5 to 2 m and a minimum thickness of 0.3 to 1 m after unfolding, a chord length of 5 to 10 m, and a wingspan of 3 to 5 m.

10. The carrier flexible configuration changing device according to claim 1, characterized in that: The inflatable nose cone (1) and the inflatable hang glider (2) are seamlessly connected or integrally formed with the fuselage in a smooth transition manner.

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