CN116399184A - Carrier rocket tail section structure and carrier rocket - Google Patents

Abstract

The invention provides a carrier rocket tail section structure and a carrier rocket, wherein the carrier rocket tail section structure comprises: the upper support frame, the middle frame and the lower support frame are used for bearing radial load and are arranged at intervals along the axial direction of the tail section structure of the carrier rocket; the two ends of at least one longitudinal support piece in the plurality of longitudinal support pieces are respectively connected with the upper support frame and the middle frame, and the two ends of at least one longitudinal support piece are respectively connected with the middle frame and the lower support frame; the skin is arranged on the longitudinal supporting piece and is used for wrapping the upper supporting frame, the middle frame, the lower supporting frame and the longitudinal supporting piece; the connecting support is arranged on the longitudinal supporting piece and is positioned outside the accommodating cavity; the connecting support is used for being connected with a landing supporting mechanism of the carrier rocket. According to the invention, the connecting support is arranged, so that the landing support mechanism can be quickly installed on the tail section, and is convenient to detach and maintain, and the installation efficiency and maintenance efficiency of the carrier rocket are further improved.

Description

Carrier rocket tail section structure and carrier rocket

Technical Field

The invention relates to the technical field of carrier rockets, in particular to a carrier rocket tail section structure and a carrier rocket.

Background

At present, with the rapid development of aerospace science and technology, world aerospace has entered a new stage represented by large-scale internet constellation, space resource development and utilization, manned moon detection, large-scale deep space detection and the like, and the demand of people for entering space is rapidly increased. If a disposable carrier rocket is used for launching tasks, the launching cost and the carrier rocket productivity are very challenging. The repeated use is a necessary choice for reducing the launching cost and coping with the productivity requirement, is the key development direction of the current carrier rocket, and is the basis for entering and exiting space in the future in a large scale and with low cost. Meanwhile, the development of the technology of reusing the carrier rocket can also effectively support the realization of the landing and take-off and return tasks of the human body from the ground to the earth.

The reusable carrier rocket is an aerospace craft which can repeatedly come and go to the earth and space and can execute certain tasks as required and return to the ground; according to the lifting mode, the lifting device can be divided into a vertical lifting mode, a vertical taking-off and horizontal landing mode and a horizontal lifting mode; the vertical take-off and landing mode generally adopts a traditional carrier rocket configuration, a landing supporting mechanism, a pneumatic speed reduction and control mechanism, a control system device for recovering related devices and the like are added, the reverse thrust speed reduction of the pneumatic and main engines is utilized in the returning process, and finally, the vertical landing is realized by means of the buffer of the landing supporting mechanism; the mode inherits the configuration design of the traditional carrier rocket, has higher integral structure efficiency of the rocket, low requirement on landing points and wider application range, and is particularly suitable for landing and taking off of future extraterrestrial stars.

The tail section is used as a main section of the reusable carrier rocket and is generally positioned at the rear end of the carrier rocket and used for connecting the engine frame and the propellant storage tank, so that not only is a good temperature environment and a good mechanical environment provided for instruments and equipment in a cabin needed, but also the tail section is a main bearing position of concentrated force transmitted by the landing support mechanism; the tail section of the existing carrier rocket is usually fixedly connected with the landing supporting mechanism in a welding mode and the like, and a structure matched with the landing supporting mechanism alone does not exist, so that the landing supporting mechanism is inconvenient to install, detach and maintain on the tail section, and the installation efficiency and maintenance efficiency of the carrier rocket are further reduced.

Disclosure of Invention

The invention provides a carrier rocket tail section structure and a carrier rocket, which are used for solving the problems that the tail section of the carrier rocket in the prior art is not provided with a structure which is matched with a landing supporting mechanism independently, so that the landing supporting mechanism is inconvenient to mount and dismount on the tail section, and the mounting efficiency and the maintenance efficiency of the carrier rocket are further reduced.

In order to solve the above problems, according to one aspect of the present invention, there is provided a tail section structure of a launch vehicle, comprising: the upper support frame, the middle frame and the lower support frame are used for bearing radial load and are sequentially arranged at intervals along the axial direction of the tail section structure of the carrier rocket; the plurality of longitudinal supporting pieces are arranged, two ends of at least one longitudinal supporting piece in the plurality of longitudinal supporting pieces are respectively connected with the upper supporting frame and the middle frame, two ends of at least one longitudinal supporting piece are respectively connected with the middle frame and the lower supporting frame, and the plurality of longitudinal supporting pieces bear axial loads together; the skin is arranged on the longitudinal supporting piece and coats the upper supporting frame, the middle frame, the lower supporting frame and the longitudinal supporting piece to form a containing cavity; the connecting support is arranged on the longitudinal supporting piece and is positioned outside the accommodating cavity; the connecting support is used for being connected with a landing supporting mechanism of the carrier rocket.

Further, the number of the middle frames is at least two, and the middle frames comprise an upper middle frame and a lower middle frame which are arranged at intervals along the axial direction of the tail section structure of the carrier rocket; the middle upper frame is fixedly connected with the upper support frame through a longitudinal support piece, and the middle lower frame is fixedly connected with the lower support frame through a longitudinal support piece.

Further, the upper frame is formed by rolling and bending two half frames of aluminum alloy plates, and the tensile strength of the aluminum alloy plates is not lower than 420MPa.

Further, the middle lower frame is formed by rolling and bending four quarter frames by aluminum alloy plates, the tensile strength of the aluminum alloy plates is not lower than 420MPa, and the thickness of the aluminum alloy plates is 2-3mm.

Further, at least one longitudinal support member of the plurality of longitudinal support members is a support beam, and the support beam is sequentially connected with the upper support frame, the middle frame and the lower support frame; the connecting support is arranged on the supporting beam; the plurality of longitudinal supporting pieces comprise a plurality of supporting stringers, two ends of one part of the supporting stringers are respectively connected with the upper supporting frame and the middle frame, and two ends of one part of the supporting stringers are respectively connected with the middle frame and the lower supporting frame.

Further, each three supporting beams form a main supporting part, wherein the supporting beam in the middle is a main beam, two supporting beams respectively positioned at two sides of the main beam are a first auxiliary beam and a second auxiliary beam, the centroid of the main beam, the centroid of the first auxiliary beam and the centroid of the second auxiliary beam are coplanar to form a first positioning surface, the intersection point of the central axis of the tail section structure of the carrier rocket and the first positioning surface is used as a circle center, the connecting line of the centroid of the first auxiliary beam and the circle center is a first diameter, the connecting line of the centroid of the main beam and the circle center is a main diameter, the connecting line of the centroid of the second auxiliary beam and the circle center is a second diameter, the included angle between the first diameter and the main diameter is the same as the included angle between the second diameter and the main diameter, and the degree range is 5-7 degrees.

Further, each three supporting beams form a main supporting part, wherein the supporting beam positioned in the middle is a main beam, two supporting beams positioned at two sides of the main beam are a first auxiliary beam and a second auxiliary beam respectively, and the connecting support is connected and fixed with the main beam through keys; the connecting support is a plurality of, and a plurality of connecting support are arranged along the circumference interval of covering, and the main support portion is a plurality of, and a plurality of connecting support and a plurality of main support portion one-to-one setting.

Further, the projection of the centroid of the supporting stringer on the first positioning surface is a projection point, the connecting line of the projection point and the circle center is a projection line, and the included angle between the first diameter or the second diameter and the adjacent projection line is 8-10 degrees.

Further, the plurality of support stringers are provided, the plurality of support stringers with two ends respectively connected with the upper support frame and the middle frame are provided as one group, and the plurality of support stringers with two ends respectively connected with the middle frame and the lower support frame are provided as another group; the centers of a plurality of supporting stringers in the same group are coplanar to form a second positioning surface, the intersection point of the central axis of the tail section structure of the carrier rocket and the second positioning surface is taken as the center, the connecting lines of the centers of two adjacent supporting stringers are respectively a first side and a second side, and the included angle between the first side and the second side is 9-11 degrees.

Further, the longitudinal support piece is an aluminum alloy forging, and the tensile strength of the longitudinal support piece is not lower than 600MPa.

Further, the tail section structure of the carrier rocket further comprises a hatch door, a hatch opening used for communicating the accommodating cavity is formed in the skin, and the hatch door is arranged at the hatch opening and used for opening and closing the hatch opening.

Further, the hatch is a plurality of, and a plurality of hatches are arranged on the skin at intervals, and the hatch is a plurality of, and a plurality of hatches are arranged in one-to-one correspondence.

Further, the upper supporting frame and the lower supporting frame are formed by stretch bending extruded sections of aluminum alloy materials, and the tensile strength of the aluminum alloy materials is not lower than 600MPa.

Further, the skin is formed by overlapping an aluminum alloy plate with the thickness of 1.2-1.5 mm; the connecting support is formed by forging TC4 titanium alloy materials.

Further, the connection support includes: the support plate is in butt joint with the skin; the connecting key is arranged on one surface of the supporting plate facing the skin and penetrates through the skin; the connecting key is matched with the longitudinal supporting piece to fixedly connect the support; the connecting part is arranged on one surface of the supporting plate, which is away from the skin, and is used for being connected with a landing supporting mechanism of the carrier rocket.

According to another aspect of the invention, there is provided a launch vehicle comprising a launch vehicle tail section structure as described above.

By applying the technical scheme of the invention, the invention provides a carrier rocket tail section structure, which comprises the following components: the upper support frame, the middle frame and the lower support frame are used for bearing radial load and are sequentially arranged at intervals along the axial direction of the tail section structure of the carrier rocket; the plurality of longitudinal supporting pieces are arranged, two ends of at least one longitudinal supporting piece in the plurality of longitudinal supporting pieces are respectively connected with the upper supporting frame and the middle frame, two ends of at least one longitudinal supporting piece are respectively connected with the middle frame and the lower supporting frame, and the plurality of longitudinal supporting pieces bear axial loads together; the skin is arranged on the longitudinal supporting piece and coats the upper supporting frame, the middle frame, the lower supporting frame and the longitudinal supporting piece to form a containing cavity; the connecting support is arranged on the longitudinal supporting piece and is positioned outside the accommodating cavity; the connecting support is used for being connected with a landing supporting mechanism of the carrier rocket. According to the invention, the landing support mechanism of the carrier rocket is connected with the connecting support, so that the tail section structure of the carrier rocket is provided with a structure which is independently matched with the landing support mechanism, the rapid installation, convenient disassembly and maintenance of the landing support mechanism on the tail section are realized, and the installation efficiency and the maintenance efficiency of the carrier rocket are further improved; the tail section structure of the carrier rocket provided by the invention has the advantages of small occupied space, high structural strength and small section mass, and the tail section structure of the carrier rocket provided by the invention has good pneumatic appearance and strong applicability by arranging the longitudinal supporting piece in the accommodating cavity; the invention can also provide tail section structural support for the reusable carrier rocket.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention. In the drawings:

FIG. 1 shows a specific structural schematic diagram of a tail section structure of a launch vehicle according to an embodiment of the present invention;

FIG. 2 is a schematic view showing the specific structures of an upper support frame, a middle frame and a lower support frame according to an embodiment of the present invention;

FIG. 3 is a schematic view showing a specific structure of a support beam according to an embodiment of the present invention;

FIG. 4 shows a specific structural schematic of a skin provided by an embodiment of the present invention;

fig. 5 shows a schematic view of the front structure of a door provided by an embodiment of the present invention;

fig. 6 shows a schematic view of the back structure of a door provided by an embodiment of the invention;

fig. 7 is a schematic perspective view of a connection support according to an embodiment of the present invention;

fig. 8 shows a schematic view of the connection mount of fig. 7 at another angle.

Wherein the above figures include the following reference numerals:

10. an upper support frame;

20. a middle frame; 21. an upper frame; 22. a middle lower frame;

30. a lower support frame;

40. a longitudinal support; 41. a support beam; 42. supporting the stringers; 43. a main support part; 431. a main beam; 432. a first secondary beam; 433. a second secondary beam;

50. a skin; 51. a receiving chamber; 52. a hatch;

60. the connecting support is connected; 61. a support plate; 62. a connecting key; 63. a connection part;

70. and (5) a cabin door.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

As shown in fig. 1 to 8, an embodiment of the present invention provides a tail section structure of a carrier rocket, including: upper support frame 10, intermediate frame 20, lower support frame 30, longitudinal support 40, skin 50, and connection mount 60;

the upper support frame 10, the middle frame 20 and the lower support frame 30 are used for bearing radial load and are sequentially arranged at intervals along the axial direction of the tail section structure of the carrier rocket;

the plurality of longitudinal supporting pieces 40 are provided, two ends of at least one longitudinal supporting piece 40 in the plurality of longitudinal supporting pieces 40 are respectively connected with the upper supporting frame 10 and the middle frame 20, two ends of at least one longitudinal supporting piece 40 are respectively connected with the middle frame 20 and the lower supporting frame 30, and the plurality of longitudinal supporting pieces 40 bear axial loads together;

the skin 50 is disposed on the longitudinal support 40, and the skin 50 covers the upper support frame 10, the middle frame 20, the lower support frame 30, and the longitudinal support 40 to form the accommodating chamber 51;

the connection support 60 is provided on the longitudinal support 40 and is located outside the housing cavity 51; the connection mount 60 is for connection to a landing support mechanism of a launch vehicle.

The landing support mechanism of the carrier rocket is connected with the connecting support 60, so that the tail section of the carrier rocket is structurally provided with a structure which is independently matched with the landing support mechanism, the rapid installation, convenient disassembly and maintenance of the landing support mechanism on the tail section are realized, and the installation efficiency and the maintenance efficiency of the carrier rocket are further improved; the tail section structure of the carrier rocket provided by the invention has the advantages of small occupied space, high structural strength and small section mass, and the longitudinal support piece 40 is arranged in the accommodating cavity 51, so that the tail section structure of the carrier rocket provided by the invention has good pneumatic appearance and strong applicability; the invention can also provide tail section structural support for the reusable carrier rocket.

In one embodiment of the present invention, as shown in fig. 1, the upper support frame 10 and the lower support frame 30 are respectively provided with a plurality of interfaces for connecting with other sections of the carrier rocket, and the plurality of interfaces are arranged on the upper support frame 10 and the lower support frame 30 at intervals. By arranging a plurality of opposite interfaces, the subsequent butt joint installation of the tail section structure of the carrier rocket on the carrier rocket is facilitated; in another embodiment of the present invention, the plurality of docking interfaces comprise docking bolt holes and docking guide pin holes, and 36 phi 13mm docking bolt holes and 4 phi 14.5mm docking guide pin holes are formed on the upper support frame 10 and the lower support frame 30.

In one embodiment of the present invention, the skin 50 is fixed to the upper support frame 10, the middle frame 20, the lower support frame 30 and the longitudinal support 40 by riveting, so as to ensure that the fixing strength of the skin 50 meets the actual aerospace requirement.

As shown in fig. 2, the number of intermediate frames 20 is at least two, including an intermediate frame 21 and an intermediate frame 22, and the intermediate frame 21 and the intermediate frame 22 are arranged at intervals along the axial direction of the tail section structure of the carrier rocket; the upper and lower frames 21 and 22 are fixedly connected with the upper and lower support frames 10 and 30 through the longitudinal supports 40 and 40, respectively. By providing the upper frame 21 and the lower frame 22, the strength and rigidity of the tail section structure of the carrier rocket in the radial direction are further increased.

Specifically, as shown in fig. 2, the upper frame 21 is formed by rolling and bending an aluminum alloy plate, and the tensile strength of the aluminum alloy plate is not lower than 420MPa, and the upper frame 21 is formed by two half frames having an "Ω" shape in cross section. The arrangement is convenient for processing the upper middle frame 21, thereby reducing the cost and ensuring that the strength of the upper middle frame 21 meets the actual use requirement.

It should be noted that: in one embodiment of the present invention, the two half frames are formed by connecting joint backer plates to ensure the connection strength of the two half frames.

Specifically, as shown in FIG. 2, the middle lower frame 22 is formed by a cross-sectional shape of "C", the middle lower frame 22 is formed by four quarter frames formed by roll bending aluminum alloy plates, the tensile strength of the aluminum alloy plates is not lower than 420MPa, and the thickness of the aluminum alloy plates is 2-3mm. The arrangement is convenient for processing the middle lower frame 22, thereby reducing the cost and ensuring that the strength of the middle lower frame 22 meets the actual use requirement.

As shown in fig. 1 and 3, at least one longitudinal support 40 among the plurality of longitudinal supports 40 is a support beam 41, and the support beam 41 is sequentially connected with the upper support frame 10, the middle frame 20, and the lower support frame 30; the connection support 60 is provided on the support beam 41; the plurality of longitudinal supports 40 include a plurality of support stringers 42, a portion of the support stringers 42 having ends respectively connected to the upper support frame 10 and the intermediate frame 20, and a portion of the support stringers 42 having ends respectively connected to the intermediate frame 20 and the lower support frame 30. By arranging the support beam 41, the axial load of the tail section structure of the carrier rocket can be effectively supported; by arranging the support stringers 42, the strength and rigidity of the tail section structure of the carrier rocket in the axial direction are further improved, and meanwhile the integral installation of the tail section structure of the carrier rocket is facilitated.

In one embodiment of the present invention, as shown in fig. 1, two ends of a plurality of support stringers 42 are respectively connected to the upper and lower middle frames 21 and 22, and the plurality of support stringers 42 are spaced apart to effectively connect and support the upper and lower middle frames 21 and 22.

It should be noted that; the lengths of the supporting stringers 42 and the supporting beams 41 can be flexibly adjusted according to the size and the length of the tail section, and the number and the assembly angle of the supporting stringers and the supporting beams are variable; the number and location of intermediate frames 20 may vary, but at least one intermediate frame 20 is required to support the connection mount 60.

As shown in fig. 1, each three supporting beams 41 form a main supporting portion 43, wherein the supporting beam 41 in the middle is a main beam 431, two supporting beams 41 respectively located at two sides of the main beam 431 are a first auxiliary beam 432 and a second auxiliary beam 433, the centroid of the main beam 431, the centroid of the first auxiliary beam 432 and the centroid of the second auxiliary beam 433 are coplanar to form a first positioning surface, the intersection point of the central axis of the tail section structure of the carrier rocket and the first positioning surface is used as a center of a circle, the connecting line of the centroid of the first auxiliary beam 432 and the center of the circle is used as a first diameter, the connecting line of the centroid of the main beam 431 and the center of the circle is used as a main diameter, the connecting line of the centroid of the second auxiliary beam 433 and the center of a circle is used as a second diameter, the included angle between the first diameter and the main diameter is the same as the included angle between the second diameter and the main diameter, and the degree range is 5-7 degrees. By arranging the main supporting parts 43, the excessive number of the supporting beams 41 is maximally avoided under the condition of ensuring the effective bearing of the axial load on the tail section structure of the carrier rocket, thereby facilitating the simplification and the weight reduction of the whole tail section structure of the carrier rocket. By setting the included angle between the first diameter and the main diameter to be the same as the included angle between the second diameter and the main diameter, the auxiliary supporting effect of the first auxiliary beam 432 and the second auxiliary beam 433 is effectively ensured.

It should be noted that: as shown in fig. 1, the first auxiliary beam 432 and the second auxiliary beam 433 are integrally installed towards the intersection point of the central axis of the tail section structure of the carrier rocket and the first positioning surface, i.e. towards the center of a circle, so that the uniformity of the overall gravity center distribution of the main support part 43 is ensured.

As shown in fig. 1, each three support beams 41 form a main support portion 43, wherein the support beam 41 located in the middle is a main beam 431, and two support beams 41 located at two sides of the main beam 431 are a first auxiliary beam 432 and a second auxiliary beam 433, respectively, and the connection support 60 is fixedly connected with the main beam 431 in the main support portion 43 through a key; the connecting support 60 is a plurality of, and a plurality of connecting support 60 are arranged along the circumference interval of the covering 50, and the main support portion 43 is a plurality of, and a plurality of connecting support 60 and a plurality of main support portions 43 are corresponding one by one and are set up. By arranging a plurality of connecting supports 60, flexible adaptation to a plurality of landing support mechanisms on the carrier rocket is realized; through setting up a plurality of connection support 60 and a plurality of main support portion 43 one-to-one, realized the effective support to each connection support 60, and then increased carrier rocket tail section structure and a plurality of landing supporting mechanism's cooperation work effect, provide the structure guarantee for the reuse of follow-up carrier rocket.

Specifically, the projection of the centroid of the support stringer 42 on the first positioning surface is a projection point, the line connecting the projection point and the center of the circle is a projection line, and the included angle between the first diameter or the second diameter and the adjacent projection line is 8-10 degrees. By arranging the included angle between the first diameter or the second diameter and the adjacent projection line, the position of the main supporting part 43 relative to the supporting stringer 42 is effectively limited while the supporting effect is met, so that the distribution of the main supporting part 43 and the supporting stringer 42 is more reasonable, and the overall weight distribution of the tail section structure of the carrier rocket is more reasonable and uniform (for example, the gravity center is positioned on the central axis).

In one embodiment of the invention, the angle between the first or second diameter and the adjacent projection line is preferably 9 degrees.

As shown in fig. 1, the number of the support stringers 42 is plural, and the number of the support stringers 42 connected to the upper support frame 10 and the intermediate frame 20 at both ends is one group, and the number of the support stringers 42 connected to the intermediate frame 20 and the lower support frame 30 at both ends is another group; the centroids of the supporting stringers 42 in the same group are coplanar to form a second positioning surface, the intersection point of the central axis of the tail section structure of the carrier rocket and the second positioning surface is taken as the center, the connection lines between the centroids of two adjacent supporting stringers 42 and the center are respectively a first side and a second side, and the included angle between the first side and the second side is 9-11 degrees. The arrangement can maximally reduce the number of the supporting stringers 42 on the premise of ensuring that the supporting effect meets the actual use requirement, so that the integral structure of the tail section of the carrier rocket is simplified and lightened; and the weight distribution of the whole structure of the tail section of the carrier rocket is more reasonable.

In one embodiment of the invention, the angle between the first edge and the second edge is preferably 10 degrees.

In another embodiment of the present invention, as shown in fig. 1, a plurality of support stringers 42, each having two ends connected to the upper frame 21 and the lower frame 22, respectively, are also formed as a group, and the installation positions of the three different groups of support stringers 42 are arranged in a collinear manner, so as to ensure the supporting effect of the support stringers 42.

Specifically, the longitudinal support 40 is an aluminum alloy forging, and its tensile strength is not lower than 600MPa. By setting the material of the longitudinal support 40, the processing and molding of the longitudinal support 40 are facilitated, and the cost of the longitudinal support 40 is reduced.

As shown in fig. 4, 5 and 6, the tail section structure of the carrier rocket further comprises a hatch 70, a hatch 52 for communicating with the accommodating cavity 51 is formed in the skin 50, and the hatch 70 is arranged at the hatch 52 for opening and closing the hatch 52. By providing the door 70, personnel or other instruments can directly enter the accommodating cavity 51 from the tail section structure of the carrier rocket, thereby facilitating subsequent inspection and equipment installation of related instruments.

Specifically, the plurality of hatches 52 are provided on the skin 50 at intervals, the plurality of hatches 70 are provided, and the plurality of hatches 70 are provided in one-to-one correspondence with the plurality of hatches 52. Different functions are achieved by different designs for different hatches 52. Structural support is provided for the division of the function of the subsequent cabin door.

In one embodiment of the invention, the number of doors 70 is three, of which two doors 70 have a specific size of 490mm x 450mm (the size of the hatch 52 is adapted accordingly), said two doors being pass-through doors for the ingress and egress of personnel; the specific dimensions of the other door 70 are 496mm x 312mm (the dimensions of the hatch 52 are adapted accordingly), which is used for the installation and inspection of the relevant instruments.

It should be noted that; the present invention provides a tail section structure of a carrier rocket, which is constructed by sequentially installing a support beam 41, a support stringer 42 and an intermediate frame 20 based on an upper support frame 10 and a lower support frame 30 during assembly, then installing a skin 50, fixing the upper support frame 10, the intermediate frame 20, the lower support frame 30 and a longitudinal support 40 into one body by using screws and rivets, finally installing a hatch door 70 on a hatch 52 by using screws, and fixing a connection bracket 60 on a main beam 431 by using screws.

Specifically, the upper support frame 10 and the lower support frame 30 are each formed by stretch bending an extruded profile of an aluminum alloy material having a tensile strength of not less than 600MPa. By setting the materials and the processing technology of the upper support frame 10 and the lower support frame 30, the processing and forming of the upper support frame 10 and the lower support frame 30 are facilitated, and the cost of the upper support frame 10 and the lower support frame 30 is reduced.

In one embodiment of the present invention, the frame distances between the upper support frame 10, the upper middle frame 21, the lower middle frame 22 and the lower support frame 30 are arranged as follows: from the lower supporting frame 30, the frame distance is 640-460-460mm from bottom to top; the arrangement is that firstly, in order to meet the assembly coordination requirement of the telescopic rod in the landing supporting mechanism, namely, the distance between the middle lower frame 22 for bearing the connecting support 60 and the lower supporting frame 30 is 640mm; secondly, in order to ensure the uniformity of the frame distance as much as possible, so as to save process preparation, the frame distances between the upper frame 21 and the middle lower frame 22 and between the upper supporting frame 10 and the upper frame 21 are finally determined to be 460mm.

As shown in FIG. 4, skin 50 is formed by overlapping aluminum alloy sheets having a thickness of 1.2-1.5 mm; the connection mount 60 is forged from a TC4 titanium alloy material. By setting the materials and the processing technology of the connecting support 60, the connecting support 60 meets the actual use requirements, and the cost of the connecting support 60 is reduced.

As shown in fig. 7 and 8, the connection holder 60 includes: a support plate 61, the support plate 61 being in abutment with the skin 50; a connection key 62, the connection key 62 being provided on a side of the support plate 61 facing the skin 50 and penetrating through the skin 50; the connecting key 62 cooperates with the longitudinal support 40 to fixedly connect the support 60; and a connection portion 63, the connection portion 63 being provided on a side of the support plate 61 facing away from the skin 50, the connection portion 63 being for connection with a landing support mechanism of a launch vehicle. By providing the structure of the connection support 60, the whole connection support 60 tends to be simplified so as to facilitate subsequent processing and installation.

In one embodiment of the present invention, the connection support 60 is keyed to the main beam 431 in the connection 63 in the form of: the connecting key 62 passes through the skin 50 (at this time, the skin 50 needs to be provided with a hole passing through the connecting key 62 in advance), and is matched with a key slot (as shown in fig. 3, a key slot is provided in the middle of the supporting beam 41) provided on the main beam 431, and then the connecting key 62 is fixed on the supporting beam 41 by riveting or welding, so as to realize the fixed matching of the connecting support 60 and the main beam 431.

It should be noted that; in one embodiment of the present invention, as shown in fig. 8, the connection portion 63 is in the form of a hinge connection; that is, the connection support 60 is a common hinge support structure, and the hinge support is hinged with a telescopic rod in the landing support mechanism so as to buffer the back impact force during landing; the number of the connecting supports 60 is 4, and the connecting supports are uniformly distributed around the skin 50 so as to ensure the uniformity of load distribution.

The invention also provides a carrier rocket, which comprises the carrier rocket tail section structure. The carrier rocket can be reused, so that the carrier rocket can be a choice for reducing the launching cost and coping with the capacity requirement, and a structural basis is provided for large-scale and low-cost space entering and exiting in the future.

In summary, the invention provides a tail section structure of a carrier rocket and the carrier rocket, wherein the tail section structure of the carrier rocket is provided with a structure which is independently matched with a landing supporting mechanism by arranging the connecting support 60 to be connected with the landing supporting mechanism of the carrier rocket, so that the rapid installation and convenient disassembly and maintenance of the landing supporting mechanism on the tail section are realized, and the installation efficiency and maintenance efficiency of the carrier rocket are further improved; the tail section structure of the carrier rocket provided by the invention has the advantages of small occupied space, high structural strength and small section mass, and the longitudinal support piece 40 is arranged in the accommodating cavity 51, so that the tail section structure of the carrier rocket provided by the invention has good pneumatic appearance and strong applicability; the invention can also provide tail section structural support for the reusable carrier rocket.

It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments in accordance with the present application. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.

The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but should be considered part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.

In the description of the present invention, it should be understood that the azimuth or positional relationships indicated by the azimuth terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal", and "top, bottom", etc., are generally based on the azimuth or positional relationships shown in the drawings, merely to facilitate description of the present invention and simplify the description, and these azimuth terms do not indicate and imply that the apparatus or elements referred to must have a specific azimuth or be constructed and operated in a specific azimuth, and thus should not be construed as limiting the scope of protection of the present invention; the orientation word "inner and outer" refers to inner and outer relative to the contour of the respective component itself.

Spatially relative terms, such as "above … …," "above … …," "above … …," "upper" and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.

In addition, the terms "first", "second", etc. are used to define the components, and are only for convenience of distinguishing the corresponding components, and the terms have no special meaning unless otherwise stated, and therefore should not be construed as limiting the scope of the present invention.

The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (16)

1. A launch vehicle tail section structure comprising:

the carrier rocket tail section structure comprises an upper supporting frame (10), a middle frame (20) and a lower supporting frame (30), wherein the upper supporting frame (10), the middle frame (20) and the lower supporting frame (30) are used for bearing radial loads and are sequentially arranged at intervals along the axial direction of the carrier rocket tail section structure;

the plurality of longitudinal supports (40), wherein at least one longitudinal support (40) of the plurality of longitudinal supports (40) is respectively connected with the upper support frame (10) and the middle frame (20), at least one longitudinal support (40) is respectively connected with the middle frame (20) and the lower support frame (30), and the plurality of longitudinal supports (40) bear axial load together;

a skin (50) disposed on the longitudinal support (40), the skin (50) covering the upper support frame (10), the intermediate frame (20), the lower support frame (30) and the longitudinal support (40) to form a receiving cavity (51);

-a connection support (60), said connection support (60) being arranged on said longitudinal support (40) and being located outside said housing cavity (51); the connecting support (60) is used for being connected with a landing support mechanism of the carrier rocket.

2. The tail section structure of a carrier rocket according to claim 1, wherein the number of the intermediate frames (20) is at least two, and the intermediate frames comprise an intermediate upper frame (21) and an intermediate lower frame (22), and the intermediate upper frame (21) and the intermediate lower frame (22) are arranged at intervals along the axial direction of the tail section structure of the carrier rocket; the middle upper frame (21) is fixedly connected with the upper support frame (10) through the longitudinal support piece (40), and the middle lower frame (22) is fixedly connected with the lower support frame (30) through the longitudinal support piece (40).

3. The tail section structure of a carrier rocket according to claim 2, wherein the upper frame (21) is composed of two half frames having a cross-sectional shape of "Ω", the half frames being formed by roll bending aluminum alloy plates having a tensile strength of not less than 420MPa.

4. The tail section structure of a carrier rocket according to claim 2, wherein the middle lower frame (22) is formed by rolling four quarter frames, the cross section is C-shaped, the quarter frames are formed by rolling aluminum alloy plates, the tensile strength of the aluminum alloy plates is not lower than 420MPa, and the thickness of the aluminum alloy plates is 2-3mm.

5. A launch vehicle tail section structure according to claim 1, wherein at least one of said longitudinal supports (40) of said plurality of longitudinal supports (40) is a support beam (41), said support beam (41) being connected in sequence to said upper support frame (10), said intermediate frame (20) and said lower support frame (30); the connecting support (60) is arranged on the supporting beam (41); the plurality of longitudinal supporting pieces (40) comprise a plurality of supporting stringers (42), wherein one part of the supporting stringers (42) are respectively connected with the upper supporting frame (10) and the middle frame (20) at two ends, and one part of the supporting stringers (42) are respectively connected with the middle frame (20) and the lower supporting frame (30) at two ends.

6. The carrier rocket tail section structure according to claim 5, wherein each three supporting beams (41) form a main supporting portion (43), wherein the supporting beam (41) in the middle is a main beam (431), two supporting beams (41) respectively located at two sides of the main beam (431) are a first auxiliary beam (432) and a second auxiliary beam (433), the centroid of the main beam (431), the centroid of the first auxiliary beam (432) and the centroid of the second auxiliary beam (433) are coplanar to form a first positioning surface, an intersection point of a central axis of the carrier rocket tail section structure and the first positioning surface is used as a center, a connecting line of the centroid of the first auxiliary beam (432) and the center is used as a first diameter, a connecting line of the centroid of the main beam (431) and the center is used as a main diameter, a connecting line of the centroid of the second auxiliary beam (433) and the center is used as a second diameter, and an included angle between the first diameter and the second diameter and the range of 5-7 degrees are the same.

7. A launch vehicle tail section structure according to claim 5, wherein each three supporting beams (41) form a main supporting portion (43), wherein the supporting beam (41) located in the middle is a main beam (431), two supporting beams (41) located at two sides of the main beam (431) are a first auxiliary beam (432) and a second auxiliary beam (433), respectively, and the connecting support (60) and the main beam (431) are fixed by key connection; the connecting supports (60) are multiple, the connecting supports (60) are arranged at intervals along the circumferential direction of the skin (50), the main supporting portions (43) are multiple, and the connecting supports (60) and the main supporting portions (43) are arranged in one-to-one correspondence.

8. A launch vehicle tail section structure according to claim 6, wherein the projection of the centroid of the support stringer (42) onto the first positioning surface is a projection point, the line connecting the projection point and the center of the circle is a projection line, and the angle between the first diameter or the second diameter and the adjacent projection line is 8-10 degrees.

9. A launch vehicle tail section structure according to claim 5, wherein the support stringers (42) are a plurality, the support stringers (42) connected at both ends to the upper support frame (10) and the intermediate frame (20) are a set, and the support stringers (42) connected at both ends to the intermediate frame (20) and the lower support frame (30) are another set;

the centers of a plurality of supporting stringers (42) in the same group are coplanar to form a second positioning surface, the intersection point of the central axis of the tail section structure of the carrier rocket and the second positioning surface is taken as the center, the connecting lines of the centers of two adjacent supporting stringers (42) and the center are respectively a first side and a second side, and the included angle between the first side and the second side is 9-11 degrees.

10. A launch vehicle tail section structure according to claim 1, wherein the longitudinal support (40) is an aluminium alloy forging, the tensile strength of which is not lower than 600MPa.

11. The tail section structure of the carrier rocket according to claim 1, further comprising a hatch (70), wherein the skin (50) is provided with a hatch (52) for communicating with the accommodating cavity (51), and the hatch (70) is arranged at the hatch (52) for opening and closing the hatch (52).

12. The launch vehicle tail section structure according to claim 11, wherein the number of the hatch (52) is plural, the plurality of hatch (52) are arranged on the skin (50) at intervals, the number of the hatch (70) is plural, and the plurality of hatch (70) are arranged in one-to-one correspondence with the plurality of hatch (52).

13. The tail section structure of a carrier rocket according to claim 1, wherein the upper support frame (10) and the lower support frame (30) are formed by stretch bending extruded sections of aluminum alloy materials, and the tensile strength of the aluminum alloy materials is not lower than 600MPa.

14. A launch vehicle tail section structure according to claim 1, wherein the skin (50) is lap-formed from aluminium alloy sheet having a thickness of 1.2-1.5 mm; the connecting support (60) is formed by forging TC4 titanium alloy materials.

15. A launch vehicle tail section structure according to claim 1, wherein said connecting support (60) comprises:

a support plate (61), the support plate (61) abutting the skin (50);

a connection key (62), the connection key (62) being provided on a face of the support plate (61) facing the skin (50) and penetrating through the skin (50); the connecting key (62) cooperates with the longitudinal support (40) to fix the connecting support (60);

the connecting part (63) is arranged on one surface of the supporting plate (61) away from the skin (50), and the connecting part (63) is used for being connected with a landing supporting mechanism of the carrier rocket.

16. A launch vehicle comprising a launch vehicle tail structure as claimed in any one of claims 1 to 15.

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