Electromagnetic cover throwing system

Abstract

The invention discloses an electromagnetic polishing cover system, and relates to the technical field of electromagnetic polishing cover systems, the electromagnetic polishing cover system comprises two separable half covers, and the two half covers are buckled to form an installation space; the energy storage assembly is arranged on the transfer cabin and located in the mounting space; the energy storage assembly comprises a plurality of groups of energy storage connecting rod structures; the energy storage connecting rod structure comprises an energy storage part, a first connecting rod part and a second connecting rod part. The ends of the first connecting rod part and the second connecting rod part abut against the same half cover, and the first connecting rod part and the second connecting rod part are in transmission connection through a tuning fork connecting rod. The energy storage part is arranged between the tuning fork connecting rod and the transfer cabin and used for providing pushing force for the first connecting rod part and the second connecting rod part, so that the first connecting rod part and the second connecting rod part can push the corresponding half covers abutting against the first connecting rod part and the second connecting rod part away from the cabin section rocket body, and the system can effectively improve the safety and stability of the fairing during separation.

Description

Technical Field

[0001] The present application generally relates to the technical field of electromagnetic shield throwing systems, and specifically to an electromagnetic shield throwing system. Background Art

[0002] The fairing is an important device on a launch vehicle. Its main function is to protect the payload in the cabin from the impact of the external environment (such as aerodynamic heat, noise, micrometeorites, etc.) during the flight. At different stages of the flight mission, the fairing needs to be reliably separated to allow the payload to enter the predetermined orbit or successfully perform its mission.

[0003] So during the fairing separation process of the launch vehicle, it is very important to ensure that the half fairing does not collide with the cabin or the load. The design of the separation system must take this into account to avoid damage to the payload. Therefore, in future rocket design and launch missions, ensuring the safety, accuracy and efficiency of fairing separation will continue to be a key factor. To this end, we propose an electromagnetic fairing ejection system to solve the above problems. Summary of the invention

[0004] In view of the above-mentioned defects or deficiencies in the prior art, it is desired to provide an electromagnetic shield throwing system with high separation safety and high efficiency.

[0005] The present application provides an electromagnetic shield-discharging system, which is connected to a cabin section and a rocket body through a transfer cabin; the electromagnetic shield-discharging system comprises: two separable half shields, which are buckled together to form an installation space; An energy storage assembly, the energy storage assembly is arranged on the transfer cabin and is located in the installation space; the energy storage assembly includes a plurality of energy storage connecting rod structures; The energy storage connecting rod structure includes: an energy storage part, a first connecting rod part and a second connecting rod part; the ends of the first connecting rod part and the second connecting rod part are respectively abutted against the same half-cover, and the first connecting rod part and the second connecting rod part are connected through a tuning fork connecting rod transmission; the energy storage part is arranged between the tuning fork connecting rod and the transfer cabin, and is used to provide a driving force for the first connecting rod part and the second connecting rod part, so that the first connecting rod part and the second connecting rod part can push the corresponding half-cover abutting therewith away from the cabin section rocket body.

[0006] According to the technical solution provided in the present application, the half cover comprises: a first half cover and a second half cover, and the installation space is obtained by buckling the first half cover and the second half cover; The bottom of the first half cover and the second half cover are connected to the transfer cabin via a pin puller; the top of the first half cover and the second half cover are jointly provided with a head cone, and the head cone is used to fix the first half cover and the second half cover.

[0007] According to the technical solution provided by the present application, the energy storage component further includes: a longitudinal main beam disposed in the middle of the adapter cabin; the longitudinal main beam has two disks spaced apart along the length direction of the longitudinal main beam; multiple groups of the energy storage link structures are evenly distributed on the longitudinal main beam, and the first link portion and the second link portion within the same group of the energy storage link structures are respectively movably connected to different disks through joint supports.

[0008] According to the technical solution provided by the present application, the first link portion includes: two mutually cooperating first transverse links and a second transverse link; one end of the first transverse link is movably connected to the joint support, and the other end thereof is hinged to one end of the second transverse link and two fork ends of the tuning fork link through a first pin. A first transverse tensioning support movably connected to the end of the second transverse link away from the first transverse link; the side of the first transverse tensioning support away from the second transverse link abuts against the first half cover or the second half cover.

[0009] According to the technical solution provided by the present application, the second link portion includes: two mutually cooperating third transverse links and a fourth transverse link, one end of the third transverse link is movably connected to the joint support, and the other end thereof is hinged to one end of the fourth transverse link and the middle of two fork ends of the tuning fork link away from the first link portion through a second pin; a second transverse tensioning support is movably connected to the end of the fourth transverse link away from the third transverse link. Wherein, the third transverse link and the fourth transverse link extend in a direction close to the first half cover or the second half cover between the corresponding two fork ends, so that the second transverse tensioning support abuts against the first half cover or the second half cover.

[0010] According to the technical solution provided by the present application, the energy storage portion includes: a first longitudinal link, one end of the first longitudinal link is movably connected to two fork ends of the tuning fork link away from the first link portion, and the middle of the other end has a first receiving groove with an opening facing the bottom of the installation space, and a connecting column is arranged in the middle of the first receiving groove. A pre-tightening energy storage spring sleeved on the periphery of the connecting column and located in the first receiving groove. A second longitudinal link, one end of the second longitudinal link is connected to the bottom of the adapter cabin through a longitudinal tensioning support, and the top of the other end has a second receiving groove with an opening facing the top of the installation space, an electromagnet is arranged in the second receiving groove, and a through hole along the length direction of the second longitudinal link is formed in the middle of the electromagnet; the connecting column carries the pre-tightening energy storage spring and extends into the through hole of the electromagnet.

[0011] According to the technical solution provided in the present application, a sliding groove is provided on the top side wall of the first half cover, the bottom of the head cone is a variable diameter structure section, and the variable diameter structure section is provided with a connecting hole that matches the sliding groove; the sliding groove and the connecting hole are matched through a connecting piece to realize the connection between the first half cover and the head cone.

[0012] According to the technical solution provided in the present application, the tops of the first half cover and the second half cover are provided with grooves matching the head cone and the separate energy storage spring for installing the head cone and the separate energy storage spring; wherein, the separate energy storage spring is located at the bottom of the variable diameter structural section, and its diameter matches the bottom end face diameter of the variable diameter structural section.

[0013] According to the technical solution provided in the present application, the first half cover and the second half cover have the same shape, and the cross-sectional length of the fairing body formed when the two are buckled together gradually increases along the direction from the nose cone to the adapter cabin.

[0014] In summary, the present technical solution specifically discloses an electromagnetic shield ejection system, which includes: two detachable half-shiels and an energy storage assembly; wherein the two half-shiels are buckled together to form an installation space, an energy storage assembly is arranged inside the installation space, and the bottom of the energy storage assembly is arranged on the transfer cabin; the energy storage assembly includes multiple groups of energy storage connecting rod structures; the energy storage connecting rod structure includes: an energy storage part, a first connecting rod part and a second connecting rod part; the ends of the first connecting rod part and the second connecting rod part are respectively abutted against the same half-shield, and the first connecting rod part and the second connecting rod part are connected through a tuning fork connecting rod transmission; the energy storage part is arranged between the tuning fork connecting rod and the transfer cabin, and is used to provide a driving force for the first connecting rod part and the second connecting rod part, so that the first connecting rod part and the second connecting rod part can push the corresponding half-shield abutted therewith away from the cabin section and the rocket body.

[0015] At present, in future rocket design and launch missions, ensuring the safety, accuracy and efficiency of fairing separation will continue to be a key factor. In this application, an electromagnetic fairing ejection system is proposed, which adopts multiple groups of energy storage connecting rod structures to abut against two detachable half-covers, so that the multiple groups of energy storage connecting rod structures not only provide multi-point support for the two half-covers when they are not separated to reduce their vibration, but also store energy through the energy storage part. When the half-cover needs to be pushed out, the energy storage part provides corresponding driving force for the first connecting rod part and the second connecting rod part in each group of energy storage connecting rod structures, so that the two half-covers can be separated stably and quickly. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Other features, objects and advantages of the present application will become more apparent by reading the detailed description of non-limiting embodiments made with reference to the following drawings: Figure 1 The figure is a schematic diagram of the structure of an electromagnetic shield throwing system.

[0017] Figure 2 It is a schematic structural diagram of an energy storage component of an electromagnetic fairing system.

[0018] Figure 3 It is a sectional view of the structure at A-A of an electromagnetic fairing system.

[0019] Figure 4 It is a partial sectional view of an electromagnetic fairing system.

[0020] Figure 5 It is a schematic diagram of the connection at the nose cone of an electromagnetic fairing system.

[0021] Reference numerals in the figure: 1, adapter module; 2, fourth transverse link; 3, tuning fork link; 4, first half fairing; 41, chute; 5, second half fairing; 6, pin puller; 7, nose cone; 71, communication hole; 8, longitudinal main beam; 9, disc; 10, joint support; 11, first transverse link; 12, second transverse link; 13, first transverse tension support; 14, third transverse link; 15, second transverse tension support; 16, first longitudinal link; 161, connecting column; 17, pre-tightening energy storage spring; 18, second longitudinal link; 19, longitudinal tension support; 20, electromagnet; 21, connecting piece; 22, separate energy storage spring. Specific embodiments

[0022] The following further elaborates on the present application in conjunction with the accompanying drawings and embodiments. It can be understood that the specific embodiments described herein are only for explaining the related invention and not for limiting the invention. Additionally, it should be noted that for ease of description, only the parts related to the invention are shown in the drawings.

[0023] It should be noted that, without conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The following will elaborate on the present application in detail with reference to the drawings and embodiments.

[0024] In order to make the technical solutions of the embodiments of the present application clearer and easier to understand, the application background provided by the embodiments of the present application will be introduced below.

[0025] The fairing is an important device on a launch vehicle, and its main function is to protect the payload in the cabin from the influence of the external environment (such as aerodynamic heat, noise, micrometeoroids, etc.) during flight. At different stages of the flight mission, the fairing needs to be separated reliably so that the payload can enter the predetermined orbit or perform its mission smoothly.

[0026] So during the fairing separation process of the launch vehicle, it is very important to ensure that the half-fairing does not collide with the cabin or the load. The design of the separation system must take this into account to avoid damage to the payload. In addition, the current fairing will also have serious low-frequency vibration problems during flight, which will also affect the flight attitude of the rocket, the stability of the control system, and will also cause damage to the payload; so in future rocket design and launch missions, ensuring the vibration reduction effect of the fairing, as well as the safety, accuracy and efficiency of the half-fairing during separation will continue to be a key factor. In view of this, please refer to Figure 1 The structure diagram of an electromagnetic shield jettisoning system provided by the present embodiment is shown, and the electromagnetic shield jettisoning system is connected to the cabin section rocket body (for example, the engine) through the adapter cabin 1. Specifically, the electromagnetic shield jettisoning system comprises: two separable half shields, and the two half shields are buckled together to form an installation space; An energy storage component is arranged on the transfer cabin 1 and is located in the installation space; the energy storage component includes a plurality of energy storage connecting rod structures; The energy storage connecting rod structure includes: an energy storage part, a first connecting rod part and a second connecting rod part; the ends of the first connecting rod part and the second connecting rod part are respectively abutted against the same half cover, and the first connecting rod part and the second connecting rod part are connected by transmission through a tuning fork connecting rod 3; the energy storage part is arranged between the tuning fork connecting rod 3 and the transfer cabin 1, and is used to provide a driving force for the first connecting rod part and the second connecting rod part, so that the first connecting rod part and the second connecting rod part can push the corresponding half cover abutted therewith away from the cabin section and the rocket body.

[0027] In this embodiment, the electromagnetic fairing ejection system includes two detachable half-covers, namely a first half-cover 4 and a second half-cover 5. The two half-covers have the same shape and can be snapped together to form an installation space. At the same time, the installation space can not only accommodate energy storage components, but also can be used to place some payloads of appropriate specifications; the energy storage components are used to push the corresponding half-cover away from the cabin and the rocket body; specifically, the energy storage components include multiple groups of energy storage connecting rod structures, which can further reduce the vibration of the fairing during flight by making multi-point contact with the two half-covers.

[0028] Among them, the energy storage link structure includes: an energy storage part, a first link part, and a second link part; the first link part and the second link part within the same energy storage link structure are distributed up and down, and are transmission-connected through a tuning fork link 3 to ensure that the upper and lower link parts can be linked by pulling the tuning fork link 3; the ends of the first link part and the second link part are both abutted against the inner wall of the corresponding half cover, and the energy storage part arranged at the tuning fork link 3 and the bottom of the adapter cabin 1 provides the driving force (propulsion force) required for the movement of the first link part and the second link part, and the first link part and the second link part push out the half cover after receiving the driving force; since the ends of the first link part and the second link part need to be abutted against the inner wall of the corresponding half cover, there are also certain design requirements for the lengths of the first link part and the second link part, which need to be set according to the shape of the half cover, and no special limitation is made here.

[0029] In a preferred embodiment, refer to Figure 1 , the half cover includes: a first half cover 4 and a second half cover 5, and the installation space is obtained by buckling the first half cover 4 and the second half cover 5; The bottoms of the first half cover 4 and the second half cover 5 are connected to the adapter cabin 1 through a pull pin device 6; a head cone 7 is jointly arranged at the tops of the first half cover 4 and the second half cover 5, and the head cone 7 is used to fix the first half cover 4 and the second half cover 5; Specifically, the first half cover 4 and the second half cover 5 form a fairing body after being buckled, and the cross-sectional length of the fairing body gradually increases along the direction from the head cone 7 to the adapter cabin 1, which can also be understood as the shape shown in Figure 4 . In this way, during the separation process of the fairing body with an inclined trend, it is easier to avoid collisions with the cabin body or the load. In addition, a head cone 7 is jointly arranged at the tops of the first half cover 4 and the second half cover 5, and the head cone 7 is used to fix the first half cover 4 and the second half cover 5; in the actual application process, the head cone 7 can be connected and fixed to one of the first half cover 4 and the second half cover 5. Since the bottom of the head cone 7 is a variable diameter structural section, and grooves corresponding to the variable diameter structural section are arranged at the tops of both the first half cover 4 and the second half cover 5, after the head cone 7 is fixed to one of the half covers, the other half cover can be buckled through a tooling.

[0030] Regarding the bottom structures of the first half cover 4 and the second half cover 5, both the bottoms of the first half cover 4 and the second half cover 5 have a connecting section extending a certain degree into the installation space, and the connecting section is in interference connection with the surface of the adapter cabin 1 through the pull pin device 6 to ensure the fixation of the first half cover 4 and the second half cover 5 to the adapter cabin 1, and at the same time, it can also ensure that the first half cover 4 and the second half cover 5 can be directly separated from the adapter cabin 1 when receiving a thrust force.

[0031] It should be noted that the stable fastening of the first half-cover 4 and the second half-cover 5 comes from the structural design on the one hand and also depends on the flight environment of the rocket. For example, in the initial stage of rocket launch, the rocket is in the accelerating upward stage. At this time, the rocket needs to overcome gravity and air resistance and accelerate to the predetermined speed. The fairing will also be affected by air resistance and aerodynamic heat, etc., making the two more compact. As the rocket flies to a certain height, the rocket already has a certain kinetic energy and potential energy at this time. The separation of the fairing will not have too much impact on the flight trajectory and speed of the rocket, and the atmospheric density of the environment where the fairing is located gradually decreases at this time, and the influence of aerodynamic force and aerodynamic heat also decreases accordingly, making it easier to separate.

[0032] In a preferred embodiment, referring to Figure 2 , the energy storage assembly further includes: a longitudinal main beam 8, and the longitudinal main beam 8 is arranged in the middle of the adapter module 1; the longitudinal main beam 8 has two discs 9 spaced apart along the length direction of the longitudinal main beam 8; multiple groups of energy storage link structures are evenly distributed on the longitudinal main beam 8, and the first link part and the second link part in the same group of energy storage link structures are respectively movably connected to different discs 9 through joint supports 10.

[0033] Specifically, the adapter module 1 is a structure with a middle support disc, so the longitudinal main beam 8 can be arranged on the support disc to provide support for multiple groups of energy storage link structures; at the same time, two discs 9 are also arranged on the longitudinal main beam 8. Since it was previously mentioned that "the first link part and the second link part are essentially distributed up and down", the two discs 9 are also essentially distributed up and down, and the first link part and the second link part in each group are respectively movably connected to different discs 9 through a joint support 10. When designing the joint support 10 here, it should be noted that the distances from the multiple joint supports 10 on each disc 9 to the center of the longitudinal main beam 8 need to be ensured to be consistent, so as to make the thrust balance at each point when the half-cover is separated.

[0034] In a preferred embodiment, the first link part includes: two mutually cooperating first transverse links 11 and second transverse links 12; one end of the first transverse link 11 is movably connected to the joint support 10, and the other end thereof is hinged to one end of the second transverse link 12 and the two bifurcated ends of the tuning fork link 3 through a first pin; A first transverse tensioning support 13, and the first transverse tensioning support 13 is movably connected to the end of the second transverse link 12 away from the first transverse link 11; the side of the first transverse tensioning support 13 away from the second transverse link 12 abuts against the first half-cover 4 or the second half-cover 5.

[0035] Specifically, the first link portion is movably connected to the joint support 10 on the disk 9 near the head cone 7. The first link portion is composed of two mutually cooperating first transverse links 11 and second transverse links 12. For example, both the first transverse link 11 and the second transverse link 12 are of hollow structure, and the second transverse link 12 is of larger specification. The end of the first transverse link 11 can extend into the second transverse link 12. Both ends of the tuning fork link 3 have two bifurcated ends. The two bifurcated ends at one end of the tuning fork link 3 are respectively arranged on both sides of the second transverse link 12, and the three are connected by a first pin. That is, the first pin penetrates through the first transverse link 11 and the second transverse link 12, and then the two ends of the first pin are connected to the two bifurcated ends at one end of the tuning fork link 3, so that the first transverse link 11 and the second transverse link 12 are movably connected to the tuning fork link 3, ensuring that the first link portion and the second link portion will not jam when pushing the half cover.

[0036] Further, a first transverse tension support 13 is also provided at the end of the second transverse link 12 away from the first transverse link 11, and the two are connected by a semi-circular snap fastener. For example, the end of the second transverse link 12 is a semi-circular arc segment, and a connecting cross bar is provided on one side of the first transverse tension support 13. The connecting cross bar matches the specification of the semi-circular arc segment, so that the arc segment can be held tightly outside the connecting cross bar to realize the connection between the two. The end of the first transverse tension support 13 away from the second transverse link 12 is a structural block with a certain area, and this structural block is used to abut against the first half cover 4 or the second half cover 5.

[0037] In a preferred embodiment, the second link portion includes: a third transverse link 14 and a fourth transverse link 2. One end of the third transverse link 14 is movably connected to the joint support 10, and the other end thereof is hinged to one end of the fourth transverse link 2 and the middle of the two bifurcated ends of the tuning fork link 3 away from the first link portion through a second pin. A second transverse tension support 15 is movably connected to the end of the fourth transverse link 2 away from the third transverse link 14. Wherein, the third transverse link 14 and the fourth transverse link 2 extend towards the direction close to the first half cover 4 or the second half cover 5 between the corresponding two bifurcated ends, so that the second transverse tension support 15 abuts against the first half cover 4 or the second half cover 5.

[0038] Specifically, the second link portion includes a third transverse link 14 and a fourth transverse link 2. One end of the third transverse link 14 is movably connected to a joint support 10 provided on a disk 9 of the longitudinal main beam 8 away from the nose cone 7. The third transverse link 14, the fourth transverse link 2 and the middle parts of the two bifurcated ends of the other end of the tuning fork link 3 are hinged by a second pin. The connection here is the same as the principle of the above-mentioned second transverse link 12, the first transverse link 11 and the tuning fork link 3, only the change in the connection position with the tuning fork link 3. The third transverse link 14 and the fourth transverse link 2 are connected to the middle parts of the two bifurcated ends of the tuning fork link 3, rather than directly movably connected to its bifurcated ends (for details, see Figure 2 ), and no more details will be described here; The fourth transverse link 2 is also movably connected to the second transverse tension support 15 through a semi-circular snap buckle. Among them, the third transverse link 14 and the fourth transverse link 2 are equivalent to passing through between the two bifurcated ends of the tuning fork link 3 away from the first link portion and extending in the direction close to the first half cover 4 or the second half cover 5, so that one side of the second transverse tension support 15 away from the fourth transverse link 2 abuts against the first half cover 4 or the second half cover 5. Whether the second transverse tension support 15 or the first transverse tension support 13 specifically abuts against which half cover can be arranged according to the actual application situation.

[0039] It should be explained that in addition to having a support disk in the middle, the transfer cabin 1 is also connected between the support disk and the annular connection main body outside the transfer cabin 1 through multiple connecting beams. Correspondingly, multiple groups of energy storage link structures can be respectively arranged on the connecting beams, and the uniform distribution of multiple groups of energy storage link structures also needs to be realized in combination with the size of the installation space. For example, in the embodiment of the present application, four groups of uniformly distributed energy storage link structures are set in total, but the selection of the specific number is not limited in the embodiment of the present application.

[0040] In a preferred embodiment, see Figure 2 and Figure 3 , the energy storage portion includes: a first longitudinal link 16. One end of the first longitudinal link 16 is movably connected to the two bifurcated ends of the tuning fork link 3 away from the first link portion, and the middle part of the other end has a first receiving groove with an opening facing the bottom of the installation space, and a connecting column 161 is arranged in the middle of the first receiving groove; A pre-tightening energy storage spring 17 is sleeved on the periphery of the connecting column 161 and is located in the first receiving groove; The second longitudinal link 18 has one end connected to the bottom of the adapter module 1 through a longitudinal tension support 19, and the other end thereof has a second receiving groove with an opening facing the top of the installation space at the top. An electromagnet 20 is arranged in the second receiving groove, and a through hole along the length direction of the second longitudinal link 18 is formed in the middle of the electromagnet 20; the connecting column 161 carries the pre-tightening energy storage spring 17 and extends into the through hole of the electromagnet 20.

[0041] Specifically, one end of the first longitudinal link 16 is used for movably connecting to the two bifurcated ends of the tuning fork link 3 away from the first link portion, thereby forming a space for the third transverse link 14 to move; wherein, the connection between the first longitudinal link 16 and the tuning fork link 3 can also be movably connected through a pin shaft.

[0042] Furthermore, the specification of the first receiving groove of the first longitudinal link 16 matches the specification of the pre-tightening energy storage spring 17. In order to ensure the connection stability of the pre-tightening energy storage spring 17, a connecting column 161 is further arranged in the middle of the first receiving groove, so that the pre-tightening energy storage spring 17 can be wound around the periphery of the connecting column 161; the pre-tightening energy storage spring 17 can store energy when not activated. When the electromagnet 20 is activated (energized), the pre-tightening energy storage spring 17 will quickly release the stored energy, drive the corresponding first longitudinal link 16 to act, and at the same time drive the tuning fork link 3 to move by the acting first longitudinal link 16, thereby driving the third transverse link 14, the fourth transverse link 2, the first transverse link 11 and the second transverse link 12 to act, and pushing out the half cover.

[0043] In addition, the energy storage part further includes a second longitudinal link 18 for supporting and accommodating the pre-tightening energy storage spring 17 and the electromagnet 20. One end of the second longitudinal link 18 is movably connected to the bottom of the adapter module 1 through a longitudinal tension support 19, and the other end thereof has a second receiving groove with an opening facing the top of the installation space at the top. The second receiving groove is used for supporting the electromagnet 20, and in order to ensure the smooth cooperation between the electromagnet 20 and the pre-tightening energy storage spring 17, the length of the connecting column 161 also needs to ensure that it can carry the pre-tightening energy storage spring 17 and extend into the through hole of the electromagnet 20.

[0044] In a preferred embodiment, referring to Figure 4 and Figure 5 , a sliding groove 41 is formed in the top side wall of the first half cover 4, and the bottom of the head cone 7 is a variable diameter structure section, and a communication hole 71 matching the sliding groove 41 is formed in the variable diameter structure section; the sliding groove 41 and the communication hole 71 are matched through a connecting member 21 to realize the connection between the first half cover 4 and the head cone 7.

[0045] Specifically, it is mentioned above that "the head cone 7 can be fixedly connected to one of the first half cover 4 and the second half cover 5". Here, the first half cover 4 does not specifically limit which half cover it is. The first and the second are only for the convenience of introduction to define the two half covers, but essentially there is no absolute distinction between the first and the second. For the convenience of connecting the head cone 7, a chute 41 is provided on the top side wall of the corresponding first half cover 4. The chute 41 is not arranged horizontally or vertically, but is inclined. The specific inclination angle needs to refer to the form of the diameter-changing structure section at the bottom of the head cone 7. And at the bottom of the chute 41 (the side away from the tip of the head cone 7) is a square through-hole, so that the subsequent connecting member 21 can slide into the chute 41. Here, the connecting member 21 adopts the form of a sliding nail and a square nut. Therefore, the bottom of the chute 41 is a square through-hole. First, slide the square nut into the chute 41, and then install the head cone 7 on the first half cover 4. Then install the sliding nail so that it passes through the communication hole 71 and is screwed with the square nut, thus completing the connection between the first half cover 4 and the head cone 7. In addition, for the specific structure of the diameter-changing structure section, reference can be made to Figure 5 , the upper part of the head cone 7 is a structure similar to a regular triangle, and the bottom of the triangular structure is a diameter-changing structure section. Specifically, the shape of the diameter-changing structure section is a vertical transition section + an inclined section. Here, the transverse cross-sectional length of the inclined section gradually increases along the direction away from the head cone 7 and closer to the interior of the installation space, forming a diameter change. In this way, the assembly area of the first half cover 4, the second half cover 5 and the head cone 7 will be larger, and it will be more stable when buckling is carried out through a tooling.

[0046] In a preferred embodiment, refer to Figure 1 and Figure 5 , grooves matching the head cone 7 and the separate energy storage spring 22 are provided at the tops of the first half cover 4 and the second half cover 5 for installing the head cone 7 and the separate energy storage spring 22. Among them, the separate energy storage spring 22 is located at the bottom of the diameter-changing structure section, and its diameter matches the bottom end face diameter of the diameter-changing structure section.

[0047] Specifically, not only the head cone 7 needs to be installed on the tops of the first half cover 4 and the second half cover 5, but also a separate energy storage spring 22 needs to be installed, so that the first half cover 4 and the second half cover 5 can be separated more quickly. Here, the diameter-changing structure section will extend into the matching grooves provided on the first half cover 4 and the second half cover 5, and a position for the separate energy storage spring 22 will be reserved at the bottom of the diameter-changing structure section. When the control system activates the electromagnet 20 to perform the separation task of the first half cover 4 and the second half cover 5, the pull pin 6 no longer fixes the first half cover 4, the second half cover 5 and the adapter cabin 1. Then the entire separate energy storage spring 22 in the compressed state is no longer restricted, and it will also provide a driving force for the separation of the first half cover 4 and the second half cover 5.

[0048] Based on the above description of an electromagnetic fairing system, the working principle of the electromagnetic fairing system of the present application is as follows: First, the energy storage part, the first link part and the second link part need to be fixed to the adapter cabin 1. Subsequently, the first half fairing 4 and the nose cone 7 are connected by connectors such as slip pins and square nuts, and the separated energy storage spring 22 is placed in the corresponding groove in the first half fairing 4. Then, another second half fairing 5 is buckled with it by using a tooling. Finally, the bottoms of the first half fairing 4 and the second half fairing 5 can be connected to the adapter cabin 1 through multiple pull pins 6, completing the connection of a fairing to the adapter cabin 1.

[0049] Secondly, when actually separating the first half fairing 4 and the second half fairing 5, the rocket control system activates the electromagnet 20 when the fairing separation needs to be completed. After the electromagnet 20 is activated, the pre-tightened energy storage spring 17 cooperating with it will quickly release the stored energy and drive the tuning fork link 3 to act. Based on the foregoing introduction to the connection relationship between the tuning fork link 3 and the first transverse link 11, the second transverse link 12, and the third transverse link 14, at this time, the tuning fork link 3 will also drive the first transverse link 11, the second transverse link 12, the third transverse link 14, and the fourth transverse link 2 to act (lift upward) respectively. Due to the setting of the cross-sectional length of the fairing body itself, when each transverse link lifts upward, a thrust will be applied to the first half fairing 4 and the second half fairing 5. When the pull pins 6 no longer impose constraints on the first half fairing 4, the second half fairing 5, and the adapter cabin 1 under the thrust, the separated energy storage spring 22 is also released, accelerating the separation of the two half fairings from the adapter cabin 1 or from the cabin section rocket body. Finally, the first half fairing 4, the second half fairing 5, the nose cone 7, and the corresponding connector 21 are separated from the adapter cabin 1, completing the release of the fairing.

[0050] The above description is only the preferred embodiment of the present application and the explanation of the applied technical principles. Those skilled in the art should understand that the scope of the invention involved in the present application is not limited to the technical solution formed by the specific combination of the above technical features, and should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the inventive concept. For example, the technical solutions formed by mutually replacing the above features with the (but not limited to) technical features with similar functions disclosed in the present application.

Claims

1. An electromagnetic shield throwing system, characterized in that: The electromagnetic shield jettisoning system is connected to the cabin section and the rocket body via a transfer cabin (1); the electromagnetic shield jettisoning system comprises: two separable half shields, which are fastened together to form an installation space; An energy storage component, the energy storage component is arranged on the transfer cabin (1) and is located in the installation space; the energy storage component comprises a plurality of groups of energy storage connecting rod structures; The energy storage connecting rod structure comprises: an energy storage part, a first connecting rod part, and a second connecting rod part; the ends of the first connecting rod part and the second connecting rod part are respectively abutted against the same half cover, and the first connecting rod part and the second connecting rod part are transmission connected via a tuning fork connecting rod (3); the energy storage part is arranged between the tuning fork connecting rod (3) and the transfer cabin (1), and is used to provide a driving force for the first connecting rod part and the second connecting rod part, so that the first connecting rod part and the second connecting rod part can push the corresponding half cover abutted therewith away from the cabin section rocket body.

2. The electromagnetic shield throwing system according to claim 1, characterized in that: The half cover comprises: a first half cover (4) and a second half cover (5), and the installation space is obtained by buckling the first half cover (4) and the second half cover (5); The bottoms of the first half cover (4) and the second half cover (5) are connected to the transfer cabin (1) via a pin puller (6); the tops of the first half cover (4) and the second half cover (5) are jointly provided with a head cone (7), and the head cone (7) is used to fix the first half cover (4) and the second half cover (5).

3. The electromagnetic shield throwing system according to claim 2, characterized in that: The energy storage assembly further comprises: a longitudinal main beam (8), the longitudinal main beam (8) being arranged in the middle of the transfer cabin (1); the longitudinal main beam (8) having two circular discs (9) spaced apart along the length direction of the longitudinal main beam (8); a plurality of groups of the energy storage connecting rod structures being evenly distributed on the longitudinal main beam (8), and the first connecting rod portion and the second connecting rod portion in the same group of the energy storage connecting rod structures being movably connected to different circular discs (9) via joint supports (10).

4. The electromagnetic shield throwing system according to claim 3 is characterized in that: The first link portion comprises: two mutually cooperating first transverse links (11) and a second transverse link (12); one end of the first transverse link (11) is movably connected to the joint support (10), and the other end is hingedly connected to one end of the second transverse link (12) and two bifurcated ends of the tuning fork link (3) via a first shaft pin; A first transverse tensioning support (13), the first transverse tensioning support (13) being movably connected to an end of the second transverse connecting rod (12) away from the first transverse connecting rod (11); a side of the first transverse tensioning support (13) away from the second transverse connecting rod (12) being in contact with the first half cover (4) or the second half cover (5).

5. The electromagnetic shield throwing system according to claim 3, characterized in that: The second link portion comprises: two third transverse links (14) and a fourth transverse link (2) which cooperate with each other; one end of the third transverse link (14) is movably connected to the joint support (10), and the other end is hinged to one end of the fourth transverse link (2) and the middle part of the two bifurcated ends of the tuning fork link (3) away from the first link portion through a second shaft pin; one end of the fourth transverse link (2) away from the third transverse link (14) is movably connected to a second transverse tension support (15); The third transverse link (14) and the fourth transverse link (2) extend between the two corresponding forked ends in a direction close to the first half cover (4) or the second half cover (5), so that the second transverse tensioning support (15) abuts against the first half cover (4) or the second half cover (5).

6. The electromagnetic shield throwing system according to claim 1, characterized in that: The energy storage part comprises: a first longitudinal connecting rod (16), one end of the first longitudinal connecting rod (16) being movably connected to two bifurcated ends of the tuning fork connecting rod (3) away from the first connecting rod part, and the middle part of the other end of the first longitudinal connecting rod (16) having a first receiving groove with an opening facing the bottom of the installation space, and a connecting column (161) being arranged in the middle part of the first receiving groove; A preloaded energy storage spring (17), the preloaded energy storage spring (17) being sleeved around the connecting column (161) and located in the first receiving groove; A second longitudinal connecting rod (18), one end of which is connected to the bottom of the transfer cabin (1) via a longitudinal tensioning support (19), and the top of the other end of which is provided with a second receiving groove with an opening toward the top of the installation space, an electromagnet (20) being arranged in the second receiving groove, a through hole being formed in the middle of the electromagnet (20) along the length direction of the second longitudinal connecting rod (18); the connecting column (161) carries the preloaded energy storage spring (17) and extends into the through hole of the electromagnet (20).

7. The electromagnetic shield throwing system according to claim 2, characterized in that: A sliding groove (41) is provided on the top side wall of the first half cover (4), and the bottom of the head cone (7) is a diameter-changing structural section, and the diameter-changing structural section is provided with a connecting hole (71) that matches the sliding groove (41); the sliding groove (41) and the connecting hole (71) are matched through a connecting piece (21) to achieve the connection between the first half cover (4) and the head cone (7).

8. The electromagnetic shield throwing system according to claim 7, characterized in that: The tops of the first half cover (4) and the second half cover (5) are provided with grooves matching the head cone (7) and the separation energy storage spring (22), for mounting the head cone (7) and the separation energy storage spring (22); wherein the separation energy storage spring (22) is located at the bottom of the variable diameter structural section, and its diameter matches the bottom end face diameter of the variable diameter structural section.

9. The electromagnetic shield throwing system according to claim 2, characterized in that: The first half cover (4) and the second half cover (5) have the same shape, and the cross-sectional length of the fairing body formed by buckling the two together gradually increases in the direction from the nose cone (7) to the adapter cabin (1).

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