CN213168609U - Return capsule and recoverable satellite - Google Patents
Return capsule and recoverable satellite Download PDFInfo
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- CN213168609U CN213168609U CN202021017667.XU CN202021017667U CN213168609U CN 213168609 U CN213168609 U CN 213168609U CN 202021017667 U CN202021017667 U CN 202021017667U CN 213168609 U CN213168609 U CN 213168609U
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Abstract
The utility model relates to a reentry module and recoverable satellite, the reentry module includes: the cabin body is provided with a preset length and comprises a windward section and a tail skirt section which are sequentially distributed in the length direction of the cabin body; the windward body is arranged at one end of the cabin body in the length direction and is connected to the windward section; the leeward body is arranged at the other end of the cabin body in the length direction and is connected with the tail skirt section, in the length direction, the leeward body and the windward body are oppositely arranged, and the orthographic projection area of the leeward body is larger than that of the windward body; the tail skirt section and the windward section are arranged in an intersecting mode, the windward body points to the leeward body in the length direction, and the cross section of the tail skirt section is gradually increased. The embodiment of the utility model provides a recoverable capsule and recoverable satellite, recoverable capsule have better pneumatic stability, can guarantee the safe operation of recoverable satellite.
Description
Technical Field
The utility model relates to an aerospace technology field especially relates to a reentry module and recoverable satellite.
Background
A recoverable satellite is an artificial satellite that has a portion of its structure that returns to the ground after completing a task in orbit. The recoverable satellite is mainly used for acquiring various earth observation information data, can be brought back to the ground for analysis processing and detailed research, and is vigorously researched and developed in various countries. The return satellite mainly comprises a transmitting section, an operation section and a reentry return section, and the main task requirements of each stage are as follows:
a transmitting section: after the preparation of the satellite and the rocket in the launching field is finished, the carrier rocket sends the satellite into a preset orbit, the satellite is separated from the carrier rocket, and the satellite enters the orbit.
The operation section is as follows: the separation moment of the satellite and the rocket is taken as a time zero point of an operation section, the satellite starts to work according to a preset program, initial attitude deviation is eliminated, the day-to-day directional stable attitude of the operation section is established, reliable working conditions are provided for loads, and the space experiment of each load item is completed.
And a reentry return section: after the satellite finishes the on-orbit flight task, according to a preset program, a satellite counting tube and a ground remote control send back attitude adjusting and unlocking instructions, an engine is braked to work or the return cabin is automatically returned to the earth according to the program control instruction, a parachute is opened at a certain height, the recovery cabin carrying the recovered load is safely landed, and the recovery of the load is realized.
To accomplish this task, a recoverable satellite essentially comprises a propulsion capsule and a recoverable capsule. The propulsion cabin is mainly used for accommodating equipment such as a propellant storage tank, an engine, electronic equipment, a solar panel, an antenna and a sensor, and the return cabin is a payload accommodating space and can be used for conveying a load carried by a satellite into space and returning the load to the ground from a space track after being stored in the space environment for a period of time. The existing recoverable satellite has the disadvantages that the pneumatic stability of the recoverable capsule is poor due to the unreasonable structural design, and the safe operation of the satellite is not facilitated.
Therefore, a new re-entry capsule and re-entry satellite are needed.
SUMMERY OF THE UTILITY MODEL
The embodiment of the utility model provides a recoverable capsule and recoverable satellite, recoverable capsule have better pneumatic stability, can guarantee recoverable satellite's safe operation.
In one aspect, according to the embodiment of the utility model provides a reentry module is proposed, include: the cabin body is provided with a preset length and comprises a windward section and a tail skirt section which are sequentially distributed in the length direction of the cabin body; the windward body is arranged at one end of the cabin body in the length direction and is connected to the windward section; the leeward body is arranged at the other end of the cabin body in the length direction and is connected with the tail skirt section, in the length direction, the leeward body and the windward body are oppositely arranged, and the orthographic projection area of the leeward body is larger than that of the windward body; the tail skirt section and the windward section are arranged in an intersecting mode, the windward body points to the leeward body in the length direction, and the cross section of the tail skirt section is gradually increased.
According to an aspect of the embodiment of the present invention, the included angle between the windward section and the tail skirt section is α, wherein α is greater than or equal to 150 ° and less than or equal to 170 °; and/or the windward section and the tail skirt section are of an integrated structure.
According to the utility model discloses an aspect, follow length direction and by the windward body is directional the leeward body, the cross section of windward section increases gradually, the tail skirt section set up in the windward section length direction's main aspects department and encircleing the windward section sets up, the reentry module wholly is the blunt head and revolves into the form.
According to an aspect of the embodiment of the present invention, the windward body is arc-shaped and protrudes in a direction away from the tail skirt section; and/or the leeward body is arc-shaped plate-shaped and protrudes towards the direction far away from the windward section.
According to an aspect of the embodiment of the present invention, the cabin body includes an annular frame extending along the length direction and having a hollow shape, and an enclosure covering the outer periphery of the annular frame and forming a hollow cavity; the windward body is connected to one end of the annular frame in the length direction, the leeward body is connected to the other end of the annular frame in the length direction, and the windward body and the leeward body jointly seal the hollow cavity.
According to an aspect of the embodiments of the present invention, the ring frame includes a first ring body, a second ring body, and a plurality of stringers, the second ring body having a radial dimension greater than a radial dimension of the first ring body and spaced apart from the first ring body in the length direction; the stringers are arranged at intervals in the circumferential direction of the first ring body, and each stringer comprises a first extension section and a second extension section which are distributed in sequence and arranged in an intersecting mode in the length direction, wherein the first extension section is connected to the first ring body, and the second extension section is connected to the second ring body.
According to an aspect of the embodiment of the present invention, the ring frame further includes a reinforcing ring body, the first ring body and at least one is provided between the second ring body the reinforcing ring body, each the stringer all with the reinforcing ring body is connected.
According to an aspect of an embodiment of the present invention, the re-entry capsule further comprises a cargo compartment body, and the cargo compartment body is disposed in the hollow cavity; wherein, the cargo hold body includes tube-shape body and connecting portion, the tube-shape body have hold the chamber and with hold the opening of chamber intercommunication, connecting portion connect in opening place side and encircle the tube-shape body sets up, the cargo hold body passes through connecting portion with at least one of cabin body, the windward side body and the leeward side body is connected.
According to one aspect of the embodiment of the present invention, the cabin body is provided with a first heat insulation layer, and the first heat insulation layer covers the outer peripheral surface of the cabin body; and/or a second heat insulation layer is arranged on the windward body and is attached to the surface of the windward body far away from the leeward body in the length direction; and/or a third heat insulation layer is arranged on the leeward body and is attached to the surface of the leeward body far away from the windward body in the length direction.
In one aspect, according to the embodiment of the present invention, a recoverable satellite is provided, including: a propulsion pod; the re-entry capsule and the propulsion capsule are distributed in sequence, and the leeward body is arranged facing the propulsion capsule and is connected with the propulsion capsule through the leeward body and/or the tail skirt section of the capsule body.
According to the utility model provides a reentry module and reentry type satellite, the reentry module includes the cabin body, the windward body and the leeward body, its windward body at the reentry module during operation at first contacts with the air current, the water conservancy diversion is realized to windward section and the tail skirt section through the cabin body, because tail skirt section sets up with windward section looks intersection, can optimize the direction to the air current of reentry module when operation, make the reentry module overall arrangement satisfy the static stability requirement and have better aerodynamic stability, can avoid the emergence of the phenomenon of overturning when operation, guarantee the steady security of reentry type satellite when each stage operation.
Drawings
Features, advantages and technical effects of exemplary embodiments of the present invention will be described below with reference to the accompanying drawings.
Figure 1 is a schematic partial structure of a prior art return satellite;
fig. 2 is a schematic partial structure diagram of a recoverable satellite according to an embodiment of the present invention;
fig. 3 is a schematic view of the overall structure of the re-entry capsule according to an embodiment of the present invention;
fig. 4 is a front view of a return module according to an embodiment of the present invention;
fig. 5 is a wall pressure cloud chart corresponding to the re-entry capsule in operation according to the embodiment of the present invention;
fig. 6 is a schematic view of the airflow corresponding to the re-entry capsule in operation according to the embodiment of the present invention;
fig. 7 is a schematic diagram showing the contour relationship between the surface pressure coefficient and the space mach number of the reentry module according to the embodiment of the present invention;
fig. 8 is a schematic structural view of a ring frame according to an embodiment of the present invention;
fig. 9 is a schematic structural view of an enclosure according to an embodiment of the present invention;
fig. 10 is a schematic structural view of a cargo compartment body according to an embodiment of the present invention;
fig. 11 is a schematic structural view of a return capsule according to another embodiment of the present invention.
Wherein:
100-a re-entry capsule;
10-a cabin body; 10 a-windward section; 10 b-tail skirt section;
11-a ring frame; 111-a first ring member; 112-a second ring; 113-stringers; 113 a-a first extension; 113 b-a second extension; 114-a reinforcing ring body; 12-an enclosure; 13-a hollow cavity;
20-windward;
30-leeward body;
40-cargo compartment body; 41-a cylindrical body; 411-an accommodation chamber; 412-an opening; 42-a connecting portion;
50-a first insulating layer; 60-a second insulating layer; 70-a third insulating layer;
200-a propulsion compartment;
x-length direction.
In the drawings, like parts are provided with like reference numerals. The figures are not drawn to scale.
Detailed Description
Features and exemplary embodiments of various aspects of the present invention will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. In the drawings and the following description, at least some well-known structures and techniques have not been shown in detail in order to avoid unnecessarily obscuring the present invention; also, the dimensions of some of the structures may be exaggerated for clarity. Furthermore, the described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.
The directional terms appearing in the following description are directions shown in the drawings, and do not limit the specific structure of the reentry module and the reentry satellite of the present invention. In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "mounted" and "connected" are to be interpreted broadly, e.g., as either a fixed connection, a removable connection, or an integral connection; can be directly connected or indirectly connected. The specific meaning of the above terms in the present invention can be understood as the case may be, by those of ordinary skill in the art.
Referring to fig. 1, a recoverable satellite in the prior art mainly includes a recoverable capsule 300, a brake capsule 400, a service capsule 500 and a seal capsule 600 that are sequentially arranged along the same direction, and the recoverable capsule 300 is a cone with smooth transition, and the static stability and the pneumatic stability of the arrangement mode are poor, which is not beneficial to the safe operation of the satellite. For a better understanding of the present invention, the detailed description of the reentry module and the reentry satellite according to the embodiments of the present invention will be made with reference to fig. 2 to 11.
Referring to fig. 2, fig. 2 is a schematic structural diagram of a recoverable satellite according to an embodiment of the present invention. The recoverable satellite comprises a propulsion capsule 200 and a recoverable capsule 100, the recoverable capsule 100 and the propulsion capsule 200 are distributed in succession and connected with each other, the propulsion capsule 200 can comprise a propellant storage tank, an engine, electronic equipment, a solar sailboard, an antenna, a sensor and the like, and the propellant storage tank, the engine, the electronic equipment, the solar sailboard, the antenna, the sensor and the like can be the existing propulsion capsule structure, and the details are not repeated.
In order to better optimize the structure of the recoverable satellite and make it have better aerodynamic stability, the embodiment of the present invention further provides a recoverable capsule 100, and the recoverable satellite 100 can be produced separately as an independent component, and of course, can also be used for the recoverable satellite of the above embodiments and be a component of the recoverable satellite.
Referring to fig. 3 and 4 together, fig. 3 is a schematic view illustrating an overall structure of a re-entry capsule 100 according to an embodiment of the present invention, and fig. 4 is a front view illustrating the re-entry capsule 100 according to an embodiment of the present invention.
The embodiment of the utility model provides a reentry module 100, it includes the cabin body 10, the windward body 20 and the leeward body 30, and cabin body 10 has predetermined length and includes windward section 10a and the tail skirt section 10b that distributes in succession on the length direction X of self. The windward body 20 is disposed at one end of the nacelle body 10 in the longitudinal direction X thereof and connected to the windward section 10 a. The leeward body 30 is provided at the other end of the cabin body 10 in the length direction X and connected to the tail skirt section 10 b. In the length direction X of the cabin body 10, the windward body 20 and the leeward body 30 are arranged oppositely, and the orthographic projection area of the windward body 20 is smaller than that of the leeward body 30, wherein the tail skirt section 10b and the windward section 10a are arranged in an intersecting manner, and the cross section of the tail skirt section 10b is gradually increased from the windward body 20 to the leeward body 30 in the length direction X.
Referring to fig. 5 and fig. 6 together, fig. 5 shows a wall pressure cloud chart corresponding to the re-entry capsule 100 of the embodiment of the present invention in operation, and fig. 6 shows an airflow schematic diagram corresponding to the re-entry capsule 100 of the embodiment of the present invention in operation. As can be seen from the figure, the embodiment of the utility model provides a reentry module 100, its windward body 20 at reentry module 100 during operation at first contacts with the air current, the water conservancy diversion is realized to windward section 10a and tail skirt section 10b through cabin body 10, because the crossing setting of tail skirt section 10b and windward section 10a, can optimize the guide to the air current of reentry module 100 when the operation, make reentry module 100 have better static stability and aerodynamic stability, can avoid the operation to overturn, the emergence of indiscriminate commentaries on classics phenomenon, guarantee the security of reentry satellite when each stage operation. Meanwhile, compared with the traditional returning capsule, the arrangement mode can reduce the taper of the windward section 10a, and is more favorable for meeting the installation requirements of onboard instruments and equipment.
As an alternative embodiment, the angle α of intersection between the windward section 10a and the tail skirt section 10b is α, wherein α is greater than or equal to 150 ° and less than or equal to 170 °, that is, the angle α of intersection between the windward section 10a and the tail skirt section 10b may be any value between 150 ° and 170 °, including both end values of 150 ° and 170 °, and may be 165 °. The included angle alpha between the windward section 10a and the tail skirt section 10b is limited to be set as above, so that the aerodynamic stability of the re-entry capsule 100 can be further optimized, the resistance of the re-entry capsule 100 in operation is reduced on the basis of ensuring the diversion requirements of the windward section 10a and the tail skirt section 10b, and the safety performance of the re-entry capsule can be improved.
Referring to fig. 2 to 7 together, fig. 7 shows a surface pressure coefficient and a mach number contour line of a space of the reentry module 100 according to an embodiment of the present invention, as an optional implementation manner, the reentry module 100 according to the above embodiments of the present invention is provided with a windward body 20 pointing to the leeward body 30 along the length direction X, a cross section of the windward section 10a is gradually increased, a tail skirt section 10b is disposed at a large end of the windward section 10a in the length direction X and surrounds the windward section 10a, and the reentry module 100 is integrally in a blunt-end spiral shape. Through the setting, can make the utility model discloses the 100 surface pressure coefficient of reentry module that the embodiment provided changes the transition evenly, and stagnation position pressure is the biggest and the flow line reduces gradually. A Mach number contour map of a plurality of sections is given in a flow field, visible space bow shock waves are clear, rear body shock waves are also clear and visible, a tail separation area is obvious, and the whole flow field structure is more reasonable.
As an alternative embodiment, the windward section 10a and the tail skirt section 10b are both in a cone shape, and may be in a cone shape. Alternatively, the windward section 10a and the tail skirt section 10b are disposed coaxially with each other. Optionally, in the length direction X, the big head end of the windward section 10a is connected with the small head end of the tail skirt section 10b and arranged in an intersecting manner.
As an optional implementation manner, in the re-entry capsule 100 provided in the above embodiments of the present invention, the windward body 20 is arc-plate-shaped and protrudes in the direction away from the tail skirt section 10b, because the re-entry capsule 100 contacts with the airflow at the windward body 20 at the time of operation, the windward body 20 is set to be arc-plate-shaped and protrudes in the direction away from the tail skirt section 10b, so that the resistance of the re-entry capsule 100 during operation can be effectively reduced.
As an alternative embodiment, the leeward body 30 has an arc-shaped plate shape and protrudes in a direction away from the windward section 10 a. With the above arrangement, the aerodynamic stability of the return capsule 100 can be further optimized.
As an optional implementation manner, the re-entry capsule 100 provided in the above embodiments of the present invention has an integral structure of the windward section 10a and the tail skirt section 10b, which is easy to form and can make the pneumatic stability of the re-entry capsule 100 better.
Referring to fig. 8 and 9 together, fig. 8 shows a schematic structural diagram of the ring frame 11 according to an embodiment of the present invention, and fig. 9 shows a schematic structural diagram of the enclosure 12 according to an embodiment of the present invention. In some optional embodiments, the capsule body 10 of the return capsule 100 provided in the above embodiments includes an annular frame 11 and an enclosure 12, the annular frame 11 extends along the length direction X and is hollow, and the enclosure 12 covers the outer periphery of the annular frame 11 and forms a hollow cavity 13. The windward body 20 is connected to one end of the annular frame 11 in the length direction X, the leeward body 30 is connected to the other end of the annular frame 11 in the length direction X, and the windward body 20 and the leeward body 30 jointly enclose the hollow cavity 13. The capsule body 10 is easy to form by adopting the structural form, the balance of the quality and the strength of the capsule body can be ensured, and the performance of the returning capsule 100 is optimized.
In some alternative embodiments, the ring frame 11 comprises a first ring 111, a second ring 112 and a plurality of stringers 113, the second ring 112 having a radial dimension greater than the radial dimension of the first ring 111 and being spaced from the first ring 111 in the length direction X of the tank body 10. The plurality of stringers 113 are arranged at intervals in the circumferential direction of the first ring body 111, and the stringers 113 include a first extension 113a and a second extension 113b distributed in succession and arranged to intersect in the longitudinal direction X of the tank body 10, wherein the first extension 113a is connected to the first ring body 111, and the second extension 113b is connected to the second ring body 112. The annular frame 11 adopting the above form has a simple structure, low cost and is easy to form on the basis of meeting the performance requirement of the return capsule 100.
In a specific implementation, the number of the stringers 113 may be set according to the size requirement and/or the strength requirement of the return tank 100, and is not limited to a specific number.
Optionally, the first ring body 111 and the second ring body 112 may be both annular and coaxially disposed, and the plurality of stringers 113 are disposed at equal intervals in the circumferential direction of the first ring body 111, so that when the reentry module 100 is in operation, the stress on the periphery is balanced and is easy to control, and the reentry module 100 can operate according to a predetermined track.
In some alternative embodiments, one end of the beam 113 may be inserted into the first ring body 111 and fixedly connected to the first ring body 111, for example, welded, and the other end of the beam 113 may be inserted into the second ring body 112 and fixedly connected to the second ring body 112, for example, by using a connection method.
Optionally, the size of each of the first extending section 113a and the second extending section 113b of the stringer 113 in the length direction X of the nacelle body 10 may be set according to requirements, in some optional examples, in the length direction X of the nacelle body 10, the length of the first extending section 113a may be consistent with the length of the windward section 10a, and the length of the second extending section 113b may be consistent with the length of the tail skirt section 10b, and by the above arrangement, the molding requirements of the windward section 10a and the tail skirt section 10b of the nacelle body 10 can be better ensured, so that the returnable cabin 100 has better aerodynamic stability.
As an alternative embodiment, the intersection angle of the first extending section 113a and the second extending section 113b may be greater than or equal to 150 ° and less than or equal to 170 °, that is, the intersection angle of the first extending section 113a and the second extending section 113b may be any value between 150 ° and 170 °, including both end values of 150 ° and 170 °, and in some alternative examples, the intersection angle of the first extending section 113a and the second extending section 113b may be selected to be 165 °, specifically set according to the requirement of the intersection angle between the windward section 10a and the tail skirt section 10b of the return capsule 100 to be formed.
As an alternative embodiment, with reference to fig. 8 and 9, the annular frame 11 of the reentry module 100 according to the above embodiments further includes a reinforcing ring 114, at least one reinforcing ring 114 is disposed between the first ring 111 and the second ring 112, and each of the beams 113 is connected to the reinforcing ring 114. Because the return capsule 100 has a predetermined length and is subjected to a strong air pressure effect during operation, the strength of the annular frame 11 can be improved by arranging the reinforcing ring body 114 and limiting the connection relationship between the stringers 113 and the reinforcing ring body 114, the deformation of the return capsule 100 during operation is effectively prevented, and the aerodynamic stability of the return capsule 100 during operation is further ensured, so that the return capsule has higher safety performance.
As an alternative embodiment, the reinforcing ring body 114 may be provided with an insertion hole having a shape matching the shape of the stringer 113, and the stringer 113 may be inserted into the reinforcing ring body 114 through the insertion hole and fixed by interference fit or welding connection with the reinforcing ring body 114.
Alternatively, the number of the reinforcing ring bodies 114 may be set according to the strength requirement of the return tank 100, and may be one, two or more, as long as the performance requirement of the return tank 100 can be satisfied.
In some alternative embodiments, the return capsule 100 provided by the above embodiments can be made of an aluminum alloy material for the first ring body 111, the second ring body 112, the reinforcing ring body 114 and the stringers 113, so that the mass is light, and the aerodynamic stability of the return capsule 100 can be better.
As an alternative embodiment, the reentry module 100 provided in each of the above embodiments may be made of a skin, the shape of the enclosure 12 may match the outer contour shape of the ring frame 11 and fit the outer periphery of the ring frame 11 to form a hollow cavity 13 inside the ring frame 11, and the skin may be made of an aluminum alloy material and may have a thickness of any value between 1.5mm and 2.5mm, including 1.5mm, 2.5mm, and optionally 2 mm.
Referring to fig. 10, fig. 10 is a schematic structural diagram of a cargo compartment 40 according to an embodiment of the present invention. As an alternative embodiment, the re-entry tank 100 provided in the above embodiments further includes a cargo tank body 40, and the cargo tank body 40 is disposed in the hollow cavity 13. The cargo hold body 40 includes a cylindrical body 41 and a connecting portion 42, the cylindrical body 41 has an accommodating cavity 411 and an opening communicating with the accommodating cavity 411, the connecting portion 42 is connected to the side of the opening and disposed around the cylindrical body 41, and the cargo hold body 40 is connected to at least one of the hold body 10, the windward body 20 and the leeward body 30 through the connecting portion 42. The cargo cabin body 40 can be used for placing loads carried by the satellite, such as various plant seeds, fruit flies and the like.
In some alternative embodiments, the cargo compartment 40 may be disposed with its opening facing the leeward body 30 and removably connected to the leeward body 30 by a connection 42.
As an alternative embodiment, the leeward body 30 and the capsule body 10 can be detachably connected to each other, and by the above arrangement, it is beneficial to place the load to be carried in the returning capsule 100.
In some alternative embodiments, the cylindrical body 41 and the connecting portion 42 may be made of an aluminum alloy material, and the wall thickness of the cylindrical body 41 may be any value between 2mm and 4mm, including both 2mm and 4mm, and may be optionally 3 mm.
As an alternative embodiment, the connection portion 42 may be an end flange disposed at the periphery of the cylindrical body 41 and connected to the cylindrical body 41, and the connection portion 42 may be detachably connected to one of the cabin body 10, the windward body 20 and the leeward body 30 by a fastening member, such as a fastening screw, etc., of course, in some examples, the connection portion 42 may be connected to at least one of the cabin body 10, the windward body 20 and the leeward body 30 by welding, etc., as long as the stability requirements of fixing the cargo cabin 40 in the hollow cavity 13, ensuring the load (such as seeds, etc.) required to be fed into the space, etc. can be satisfied.
Referring to fig. 11, fig. 11 is a schematic structural view of a returning capsule 100 according to another embodiment of the present invention. In some optional embodiments, the above embodiments provide the return capsule 100, the capsule body 10 is provided with the first thermal insulation layer 50, and the first thermal insulation layer 50 is disposed to cover the outer circumferential surface of the capsule body 10. By providing the first insulating layer 50, the first insulating layer can passThe heat insulating layer 50 protects the capsule body 10, and improves the heat resistance of the capsule body 10 when the return capsule 100 is in operation. Alternatively, the first thermal barrier layer 50 may be a low density ablative material having a density of about 0.3g/cm3And the thickness is any value between 20mm and 25mm, including two end values of 20mm and 25mm, and through the arrangement, the heat resistance of the cabin body 10 can be further optimized.
As an alternative embodiment, in the return capsule 100 provided in each of the above embodiments, the windward side body 20 is provided with the second heat insulation layer 60, and the second heat insulation layer 60 is attached to the surface of the windward side body 20 away from the leeward side body 30 in the longitudinal direction X. The second heat insulating layer 60 can be used for protecting the windward body 20, and the heat resistance of the windward body 20 is improved. Alternatively, the second thermal barrier layer 60 may be a low density ablative material having a density of about 0.5g/cm3And the thickness is any value between 35mm and 45mm, including two end values of 35mm and 45mm, and can be selected to be 40cm, and through the arrangement, the heat resistance of the windward body 20 can be further optimized.
In some optional embodiments, in the return capsule 100 provided in each of the above embodiments, the leeward body 30 is provided with the third thermal insulation layer 70, and the third thermal insulation layer 70 is attached to the surface of the leeward body 30 away from the windward body 20 in the length direction X. The third heat insulation layer 70 can be used for protecting the leeward body 30 and improving the heat resistance of the leeward body 30, and optionally, the third heat insulation layer 70 can be made of a low-density ablative material with the density of about 0.3g/cm3And the thickness is any value between 20mm and 25mm, including two end values of 20mm and 25mm, and through the setting, the heat resistance of the leeward body 30 can be further optimized.
As an alternative embodiment, the mass of the return tank 100 provided in the above embodiments may be less than or equal to 175 kg. Optionally, the overall length of the returning capsule 100 in the length direction X of the capsule body 10 is any value between 1408mm and 1418mm, including both ends 1408mm and 1418mm, optionally 1413 mm. Through the arrangement, the performance of the recoverable capsule 100 can be further optimized, and the use requirement of the recoverable satellite can be better met.
As an optional implementation manner, the recoverable satellite provided in the above embodiments of the present invention has an overall mass of 250kg or less, and the overall length of the recoverable satellite in the length direction X of the capsule body 10 is any value between 1908mm and 1918mm, including two end values of 1908mm and 1918mm, and is optionally 1913 mm. Optionally, the radial dimension of the recoverable satellite is any value between 1178mm and 1188mm, including both ends 1178mm and 1188mm, optionally 1183 mm. Through the setting, the recoverable satellite has better pneumatic stability, higher safety and easy control.
To sum up, the utility model discloses a reentry module 100, including the cabin body 10 because of it, the windward body 20 and the leeward body 30, its windward body 20 at reentry module 100 during operation at first contacts with the air current, the water conservancy diversion is realized to windward section 10a and tail skirt section 10b through cabin body 10, because tail skirt section 10b intersects the setting with windward section 10a, can optimize the guide to the air current when reentry module 100 is moving, make reentry module 100 overall arrangement satisfy the static stability requirement and have better aerodynamic stability, can avoid the operation to overturn, the emergence of indiscriminate commentaries on classics phenomenon, guarantee the steady security of reentry type satellite when each stage moves. Meanwhile, compared with the traditional returning capsule 100, the arrangement mode can reduce the taper of the windward section 10a, and is more favorable for meeting the installation requirements of onboard instruments and equipment. And, through simulation analysis, the embodiment of the utility model provides a reentry module 100 sets up through above-mentioned structure, can also make reentry module 100's resistance coefficient, lift coefficient and all obtain better optimization to the moment coefficient of calculating the coordinate system initial point.
And the embodiment of the utility model provides a recoverable satellite, because of it includes the recoverable capsule 100 that above-mentioned each embodiment provided, consequently, recoverable satellite overall arrangement satisfies the static stability requirement, and when being in active service, and pneumatic stability is good, and steady security when each stage operation is higher, easily uses widely.
While the invention has been described with reference to a preferred embodiment, various modifications may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. In particular, the technical features mentioned in the embodiments can be combined in any way as long as there is no structural conflict. The present invention is not limited to the particular embodiments disclosed herein, but encompasses all technical solutions falling within the scope of the claims.
Claims (10)
1. A re-entry capsule (100), comprising:
the cabin body (10) is provided with a preset length and comprises a windward section (10a) and a tail skirt section (10b) which are sequentially distributed in the length direction (X);
a windward body (20) provided at one end of the nacelle body (10) in the length direction (X) and connected to the windward section (10 a);
the leeward body (30) is arranged at the other end of the cabin body (10) in the length direction (X) and is connected with the tail skirt section (10b), in the length direction (X), the leeward body (30) is arranged opposite to the windward body (20), and the orthographic projection area of the leeward body (30) is larger than that of the windward body (20);
wherein the tail skirt section (10b) and the windward section (10a) are arranged in an intersecting manner, the cross section of the tail skirt section (10b) is gradually increased along the length direction (X) and from the windward body (20) to the leeward body (30).
2. The return capsule (100) according to claim 1, characterised in that the angle of intersection between the windward section (10a) and the tail skirt section (10b) is α, wherein α is 150 ° or more and 170 ° or less;
and/or the windward section (10a) and the tail skirt section (10b) are of an integrated structure.
3. The re-entry capsule (100) according to claim 1, wherein the cross section of the windward section (10a) increases gradually along the length direction (X) and from the windward body (20) to the leeward body (30), the tail skirt section (10b) is arranged at the large end of the windward section (10a) in the length direction (X) and around the windward section (10a), and the re-entry capsule is overall in a shape of a blunt end spiral.
4. The re-entry capsule (100) according to claim 1, wherein the windward body (20) is arc-plate-shaped and projects in a direction away from the tail skirt section (10 b);
and/or the leeward body (30) is arc-shaped plate-shaped and protrudes in the direction far away from the windward section (10 a).
5. The return capsule (100) according to claim 1, characterised in that the capsule body (10) comprises an annular frame (11) and an enclosure (12), the annular frame (11) extending along the length direction (X) and being hollowed out, the enclosure (12) being arranged to surround the outer circumference of the annular frame (11) and forming a hollow cavity (13);
the windward body (20) is connected to one end of the annular frame (11) in the length direction (X), the leeward body (30) is connected to the other end of the annular frame (11) in the length direction (X), and the windward body (20) and the leeward body (30) jointly seal the hollow cavity (13).
6. A re-entry capsule (100) according to claim 5, characterised in that said annular frame (11) comprises a first ring (111), a second ring (112) and a plurality of stringers (113), said second ring (112) having a radial dimension greater than that of said first ring (111) and being spaced from said first ring (111) in said length direction (X);
the stringers (113) are arranged at intervals in the circumferential direction of the first ring body (111), the stringers (113) comprise a first extension (113a) and a second extension (113b) which are distributed in succession and intersect in the length direction (X), the first extension (113a) is connected to the first ring body (111), and the second extension (113b) is connected to the second ring body (112).
7. The capsule (100) according to claim 6, characterised in that said annular frame (11) further comprises a reinforcement ring (114), at least one said reinforcement ring (114) being arranged between said first ring (111) and said second ring (112), each said stringer (113) being connected to said reinforcement ring (114).
8. The reentry module (100) of claim 5, wherein the reentry module (100) further comprises a cargo tank body (40), the cargo tank body (40) being disposed in the hollow chamber (13);
wherein, the cargo compartment body (40) includes tube-shape body (41) and connecting portion (42), tube-shape body (41) have hold chamber (411) and with the opening that holds chamber (411) intercommunication, connecting portion (42) connect in the opening place side and encircle tube-shape body (41) set up, cargo compartment body (40) pass through connecting portion (42) with cabin body (10), windward side body (20) and at least one of leeward side body (30) are connected.
9. A re-entry capsule (100) according to any of claims 1 to 8, characterised in that said capsule body (10) is provided with a first thermally insulating layer (50), said first thermally insulating layer (50) being provided so as to cover the outer peripheral surface of said capsule body (10);
and/or a second heat insulation layer (60) is arranged on the windward body (20), and the second heat insulation layer (60) is attached to the surface, away from the leeward body (30), of the windward body (20) in the length direction (X);
and/or a third heat insulation layer (70) is arranged on the leeward body (30), and the third heat insulation layer (70) is attached to the surface, away from the windward body (20), of the leeward body (30) in the length direction (X).
10. A recoverable satellite, comprising:
a propulsion pod (200);
the return capsule (100) according to any of claims 1 to 9, said return capsule (100) being distributed in succession to said propulsion capsule (200), said leeward body (30) being arranged facing said propulsion capsule (200) and being connected to said propulsion capsule (200) by said leeward body (30) and/or said tail skirt section (10b) of said capsule body (10).
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| CN202021017667.XU CN213168609U (en) | 2020-06-05 | 2020-06-05 | Return capsule and recoverable satellite |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113320716A (en) * | 2021-06-16 | 2021-08-31 | 上海交通大学 | Extraterrestrial adversity lander with function of automatically adjusting foot end touch point |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113320716A (en) * | 2021-06-16 | 2021-08-31 | 上海交通大学 | Extraterrestrial adversity lander with function of automatically adjusting foot end touch point |
| CN113320716B (en) * | 2021-06-16 | 2022-08-09 | 上海交通大学 | Extraterrestrial adversity lander with function of automatically adjusting foot end touch point |
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