An electromagnetic shield throwing system

Abstract

The present application discloses an electromagnetic fairing ejection system, which relates to the technical field of electromagnetic fairing ejection systems. The electromagnetic fairing ejection system includes: two detachable half-covers, which form an installation space when the two half-covers are buckled together; an energy storage component, which is arranged on the transfer cabin and located in the installation space; the energy storage component 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-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 abutted therewith away from the cabin section and the rocket body. 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 a critical component of a launch vehicle. Its primary function is to protect the payload within the capsule from external environmental influences (such as aerodynamic heat, noise, and micrometeoroids) during flight. At different stages of the mission, the fairing must reliably separate to allow the payload to enter its intended orbit or successfully carry out its mission.

[0003] During the fairing separation process of a launch vehicle, it is extremely important to ensure that the fairing does not collide with the cabin or payload. The separation system design must take this into account to avoid damage to the payload. Therefore, ensuring the safety, accuracy, and efficiency of fairing separation will continue to be a key factor in future rocket designs and launch missions. To this end, we propose an electromagnetic fairing ejection system to address the above issues. 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 jettisoning system, which is connected to a cabin and a rocket body via a transfer cabin. The electromagnetic shield jettisoning system comprises: two detachable half shields, which form an installation space when fastened together;

[0006] An energy storage assembly, the energy storage assembly being arranged on the adapter cabin and located in the installation space; the energy storage assembly comprising a plurality of energy storage connecting rod structures;

[0007] 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.

[0008] According to the technical solution provided in this application, the half cover includes: 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;

[0009] The bottoms of the first half cover and the second half cover are connected to the transfer cabin via a pin puller; the tops of the first half cover and the second half cover are jointly provided with a nose cone, which is used to fix the first half cover and the second half cover.

[0010] According to the technical solution provided in this application, the energy storage component also includes: a longitudinal main beam, which is arranged in the middle of the transfer cabin; the longitudinal main beam has two discs spaced apart along the length direction of the longitudinal main beam; multiple groups of the energy storage connecting rod structures are evenly distributed on the longitudinal main beam, and the first connecting rod part and the second connecting rod part in the same group of the energy storage connecting rod structures are respectively movably connected to different discs through joint supports.

[0011] According to the technical solution provided in the present application, the first link portion includes: two mutually cooperating first and second transverse links; 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 the two bifurcated ends of the tuning fork link via a first shaft pin;

[0012] A first transverse tensioning support is movably connected to an end of the second transverse link away from the first transverse link; a side of the first transverse tensioning support away from the second transverse link is in contact with the first half cover or the second half cover.

[0013] 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 part of the two bifurcated ends of the tuning fork link away from the first link portion through a second shaft pin; the end of the fourth transverse link away from the third transverse link is movably connected to the second transverse tensioning support;

[0014] The third transverse link and the fourth transverse link extend between the corresponding two forked ends toward the first half cover or the second half cover, so that the second transverse tensioning support abuts against the first half cover or the second half cover.

[0015] According to the technical solution provided in the present application, the energy storage portion includes: a first longitudinal connecting rod, one end of which is movably connected to the two bifurcated ends of the tuning fork connecting rod away from the first connecting rod portion, and the middle portion of the other end of the first longitudinal connecting rod has a first receiving groove with an opening toward the bottom of the installation space, and a connecting column is provided in the middle portion of the first receiving groove;

[0016] a preloaded energy storage spring, the preloaded energy storage spring being sleeved around the connecting column and located in the first receiving groove;

[0017] A second longitudinal connecting rod, one end of the second longitudinal connecting rod is connected to the bottom of the transfer cabin through a longitudinal tensioning support, and the top of the other end thereof has a second accommodating groove with an opening toward the top of the installation space, an electromagnet is arranged in the second accommodating groove, and a through hole is formed in the middle of the electromagnet along the length direction of the second longitudinal connecting rod; the connecting column carries the pre-tightening energy storage spring and extends into the through hole of the electromagnet.

[0018] According to the technical solution provided in this 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 cooperates with the sliding groove; the sliding groove and the connecting hole cooperate with each other through a connecting piece to realize the connection between the first half cover and the head cone.

[0019] 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.

[0020] 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 transfer cabin.

[0021] To sum up, 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 against them away from the cabin section and the rocket body.

[0022] 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 uses 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 to 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

[0023] Other features, objects and advantages of the present application will become more apparent upon reading the detailed description of non-limiting embodiments made with reference to the following drawings:

[0024] Figure 1 This is a structural diagram of an electromagnetic shield throwing system.

[0025] Figure 2 This is a schematic diagram of the energy storage component structure of an electromagnetic shield throwing system.

[0026] Figure 3 This is a structural cross-sectional view of the AA portion of an electromagnetic shield ejection system.

[0027] Figure 4 This is a partial structural cross-sectional view of an electromagnetic shield throwing system.

[0028] Figure 5 This is a schematic diagram of the connection at the nose cone of an electromagnetic shield ejection system.

[0029] Numbers in the figure: 1. Transfer cabin; 2. Fourth transverse link; 3. Tuning fork link; 4. First half cover; 41. Slide groove; 5. Second half cover; 6. Pin puller; 7. Nose cone; 71. Connecting hole; 8. Longitudinal main beam; 9. Disc; 10. Joint support; 11. First transverse link; 12. Second transverse link; 13. First transverse tensioning support; 14. Third transverse link; 15. Second transverse tensioning support; 16. First longitudinal link; 161. Connecting column; 17. Preloaded energy storage spring; 18. Second longitudinal link; 19. Longitudinal tensioning support; 20. Electromagnet; 21. Connecting piece; 22. Separate energy storage spring. DETAILED DESCRIPTION

[0030] The present application will be further described in detail below with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are merely for the purpose of explaining the relevant invention and are not intended to limit the invention. It should also be noted that, for ease of description, only portions relevant to the invention are shown in the accompanying drawings.

[0031] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments in this application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0032] In order to make the technical solutions of the embodiments of the present application clearer and easier to understand, the application background of the embodiments of the present application is introduced below.

[0033] The fairing is a critical component of a launch vehicle. Its primary function is to protect the payload within the capsule from external environmental influences (such as aerodynamic heat, noise, and micrometeoroids) during flight. At different stages of the mission, the fairing must reliably separate to allow the payload to enter its intended orbit or successfully carry out its mission.

[0034] Therefore, during the separation process of the launch vehicle's fairing, it is very important to ensure that the half-flying 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 rocket's flight attitude and the stability of the control system, and will also cause damage to the payload. Therefore, in future rocket designs and launch missions, ensuring the vibration reduction effect of the fairing and the safety, accuracy and efficiency of the half-flying 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 jettison system provided by this embodiment is shown. The electromagnetic shield jettison system is connected to the cabin section (e.g., the engine) via an adapter cabin 1. Specifically, the electromagnetic shield jettison system includes: two detachable half shields, which, when fastened together, form an installation space;

[0035] Energy storage assembly, the energy storage assembly is arranged on the adapter cabin 1 and is located in the installation space; the energy storage assembly includes multiple groups of energy storage connecting rod structures;

[0036] 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 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 against them away from the cabin section and the rocket body.

[0037] 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.

[0038] Among them, the energy storage connecting rod structure includes: an energy storage part, a first connecting rod part and a second connecting rod part; the first connecting rod part and the second connecting rod part in the same energy storage connecting rod structure are equivalent to being distributed up and down, and are connected in transmission through a tuning fork connecting rod 3 to ensure that the upper and lower connecting rod parts can be linked by pulling the tuning fork connecting rod 3; the ends of the first connecting rod part and the second connecting rod part are both in contact with the inner wall of the corresponding half cover, and the energy storage part arranged at the bottom of the tuning fork connecting rod 3 and the adapter cabin 1 provides the first connecting rod part and the second connecting rod part with the driving force (pushing force) required for movement, and the first connecting rod part and the second connecting rod part push the half cover out after receiving the driving force; since the ends of the first connecting rod part and the second connecting rod part need to be in contact with the inner wall of the corresponding half cover, there are certain design requirements for the length of the first connecting rod part and the second connecting rod part, which need to be set according to the shape of the half cover, and no special limitation is made here.

[0039] In a preferred embodiment, see 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;

[0040] The bottom of the first half cover 4 and the second half cover 5 are connected to the transfer cabin 1 through a pin puller 6; the top of the first half cover 4 and the second half cover 5 are jointly provided with a nose cone 7, which is used to fix the first half cover 4 and the second half cover 5;

[0041] Specifically, the first half cover 4 and the second half cover 5 form a fairing body after being buckled together, and the cross-sectional length of the fairing body gradually increases along the direction from the nose cone 7 to the transfer cabin 1, which can also be understood as follows Figure 4The shape shown here is that the fairing body is inclined, which makes it easier to avoid collision with the cabin or load during the separation process. In addition, a nose cone 7 is provided on the top of the first half-cover 4 and the second half-cover 5. The nose cone 7 is used to fix the first half-cover 4 and the second half-cover 5. In actual application, the nose 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 nose cone 7 is a variable diameter structural section, and the tops of the first half-cover 4 and the second half-cover 5 are both provided with grooves corresponding to the variable diameter structural section, after the nose cone 7 is fixed to one of the half-covers, the other half-cover can be fastened with a tool.

[0042] Regarding the bottom structure of the first half cover 4 and the second half cover 5, the bottom of the first half cover 4 and the second half cover 5 both have a connecting section that extends to a certain extent into the installation space. The connecting section is interference-connected with the surface of the transfer cabin 1 through the pin puller 6, ensuring that the first half cover 4 and the second half cover 5 are fixed to the transfer 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 transfer cabin 1 when subjected to thrust.

[0043] It should be explained that the stable fastening of the first half-shell 4 and the second half-shell 5 is due to the structural design on the one hand, and also depends on the rocket's flight environment on the other. For example, in the early stages of a rocket launch, the rocket is in the accelerated ascent phase. At this time, the rocket needs to overcome gravity and air resistance to accelerate to a predetermined speed. The fairing is also affected by the rocket and the fairing is affected by air resistance and aerodynamic heat, making the two more compact. As the rocket reaches a certain altitude, the rocket has already acquired a certain amount of kinetic energy and potential energy. The separation of the fairing will not have a significant impact on the rocket's flight trajectory and speed. At this time, the atmospheric density of the environment in which the fairing is located gradually decreases, and the influence of aerodynamic force and aerodynamic heat is also reduced accordingly, making separation more convenient.

[0044] In a preferred embodiment, see Figure 2 The energy storage component also includes: a longitudinal main beam 8, which is arranged in the middle of the transfer cabin 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 connecting rod structures are evenly distributed on the longitudinal main beam 8, and the first connecting rod part and the second connecting rod part in the same group of energy storage connecting rod structures are respectively movably connected to different discs 9 through joint supports 10.

[0045] Specifically, the transfer cabin 1 is a structure with a central support disc, so the longitudinal main beam 8 can be set on the support disc to provide support for multiple groups of energy storage connecting rod structures; at the same time, two discs 9 are still provided on the longitudinal main beam 8. Since it is mentioned above that "the first connecting rod part and the second connecting rod part are equivalent to being distributed up and down", the two discs 9 are essentially also distributed up and down, and the first connecting rod part and the second connecting rod 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 multiple joint supports 10 on each disc 9 need to be kept consistent in size from the center of the longitudinal main beam 8, so that when the half cover is separated, the thrust at each point is balanced.

[0046] In a preferred embodiment, the first link portion 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 via a first shaft pin;

[0047] 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 is in contact with the first half cover 4 or the second half cover 5.

[0048] Specifically, the first connecting rod portion is movably connected to the joint support 10 on the disk 9 near the head cone 7, and the first connecting rod portion is composed of two first transverse links 11 and second transverse links 12 that cooperate with each other. For example, the first transverse link 11 and the second transverse link 12 are both hollow structures, and the second transverse link 12 is larger in size. The end of the first transverse link 11 can extend into the second transverse link 12; and both ends of the tuning fork link 3 have two forked ends, and the two forked ends at one end of the tuning fork link 3 are arranged on both sides of the second transverse link 12, and the three are connected by a first axle pin, that is, the first axle pin passes through the first transverse link 11 and the second transverse link 12, and then the two ends of the first axle pin are connected to the two forked 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 connecting rod portion and the second connecting rod portion will not get stuck when pushing the half cover.

[0049] Furthermore, a first transverse tensioning support 13 is provided at one end of the second transverse link 12 away from the first transverse link 11, and the two are connected by a semicircular buckle-type buckle. For example, the end of the second transverse link 12 is a semicircular arc segment, and one side of the first transverse tensioning support 13 is provided with a connecting cross bar, which matches the specifications of the semicircular arc segment, so that the arc segment can be clamped on the outside of the connecting cross bar to achieve the connection between the two; and the end of the first transverse tensioning support 13 away from the second transverse link 12 is a structural block with a certain area, which is used to abut against the first half cover 4 or the second half cover 5.

[0050] 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 hingedly connected to one end of the fourth transverse link 2 and the middle portion of the two bifurcated ends of the tuning fork link 3 away from the first link portion via a second shaft pin; the end of the fourth transverse link 2 away from the third transverse link 14 is movably connected to the second transverse tensioning support 15;

[0051] The third transverse link 14 and the fourth transverse link 2 extend between the corresponding two bifurcated ends toward 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 .

[0052] Specifically, the second link portion includes a third transverse link 14 and a fourth transverse link 2, and one end of the third transverse link 14 is movably connected to a joint support 10 provided on a disc 9 away from the head cone 7 of the longitudinal main beam 8; the third transverse link 14, the fourth transverse link 2 and the middle part of the two bifurcated ends of the other end of the tuning fork link 3 are hinged by a second shaft pin, and the connection here is the same as the principle of the second transverse link 12, the first transverse link 11 and the tuning fork link 3 mentioned above, except that the connection position with the tuning fork link 3 is changed, and the third transverse link 14 and the fourth transverse link 2 are connected to the middle part of the two bifurcated ends of the tuning fork link 3, and are not directly movably connected to their bifurcated ends (see for details). Figure 2 ), I will not go into too much detail here;

[0053] The fourth transverse link 2 is also movably connected to the second transverse tensioning support 15 through a semicircular buckle; wherein, the third transverse link 14 and the fourth transverse link 2 are equivalent to passing through the two forked ends of the tuning fork link 3 away from the first link part, and extending toward the direction close to the first half cover 4 or the second half cover 5, so that the side of the second transverse tensioning support 15 away from the fourth transverse link 2 is in contact with the first half cover 4 or the second half cover 5. Regardless of which half cover the second transverse tensioning support 15 or the first transverse tensioning support 13 is in contact with, it can be arranged according to the actual application situation.

[0054] It needs to be explained that in addition to the support disc in the middle of the adapter cabin 1, the support disc and the annular connecting body outside the adapter cabin 1 are also connected by multiple connecting beams. Accordingly, multiple groups of energy storage connecting rod structures can be arranged on the connecting beams respectively, and the size of the installation space is also needed to achieve uniform distribution of multiple groups of energy storage connecting rod structures. For example, in the embodiment of the present application, a total of four groups of uniformly distributed energy storage connecting rod structures are provided, but the selection of the specific number is not limited in the embodiment of the present application.

[0055] In a preferred embodiment, see Figure 2 and Figure 3 The energy storage portion includes: a first longitudinal connecting rod 16, one end of which is movably connected to the two bifurcated ends of the tuning fork connecting rod 3 away from the first connecting rod portion, and a first receiving groove having an opening toward the bottom of the installation space in the middle of the other end thereof, and a connecting column 161 is provided in the middle of the first receiving groove;

[0056] The preloaded energy storage spring 17 is sleeved around the connecting column 161 and located in the first receiving groove;

[0057] The second longitudinal link 18, one end of the second longitudinal link 18 is connected to the bottom of the transfer cabin 1 through a longitudinal tensioning support 19, and the top of the other end thereof has a second accommodating groove with an opening toward the top of the installation space, an electromagnet 20 is arranged in the second accommodating groove, and a through hole is formed in the middle of the electromagnet 20 along the length direction of the second longitudinal link 18; the connecting column 161 carries a pre-tightened energy storage spring 17 and extends into the through hole of the electromagnet 20.

[0058] Specifically, one end of the first longitudinal link 16 is used to be movably connected to the two forked 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.

[0059] Furthermore, the specifications of the first accommodating groove of the first longitudinal link 16 match the specifications of the pre-loaded energy storage spring 17. In order to ensure the connection stability of the pre-loaded energy storage spring 17, a connecting column 161 is further provided in the middle of the first accommodating groove, so that the pre-loaded energy storage spring 17 can be arranged around the circumference of the connecting column 161; the pre-loaded energy storage spring 17 can store energy when it is not activated. When the electromagnet 20 is activated (powered on), the pre-loaded energy storage spring 17 will quickly release the stored energy, driving the corresponding first longitudinal link 16 to move. At the same time, the moving first longitudinal link 16 drives the tuning fork link 3 to move, and then drives the third transverse link 14, the fourth transverse link 2, the first transverse link 11 and the second transverse link 12 to move, thereby pushing the half cover out.

[0060] In addition, the energy storage part also includes a second longitudinal connecting rod 18 for supporting and accommodating the pre-tensioned energy storage spring 17 and the electromagnet 20. One end of the second longitudinal connecting rod 18 is movably connected to the bottom of the transfer cabin 1 through a longitudinal tensioning support 19, and the top of the other end thereof has a second accommodating groove with an opening toward the top of the installation space. The second accommodating groove is used to support the electromagnet 20. In order to ensure that the electromagnet 20 and the pre-tensioned energy storage spring 17 can cooperate smoothly, the length of the connecting column 161 must also ensure that it can carry the pre-tensioned energy storage spring 17 into the through hole of the electromagnet 20.

[0061] In a preferred embodiment, see Figure 4 and Figure 5 A slide 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 variable diameter structure section, which is provided with a connecting hole 71 that cooperates with the slide groove 41; the slide groove 41 and the connecting hole 71 are matched through the connecting piece 21 to realize the connection between the first half cover 4 and the head cone 7.

[0062] Specifically, it is mentioned above that "the head cone 7 can be connected and fixed to one of the first half cover 4 and the second half cover 5". The first half cover 4 here does not limit which specific half cover it is. The first and second are completely for the convenience of introduction, thereby defining the two half covers, but in essence there is no absolute distinction between the first and the second. In order to facilitate the connection of the head cone 7, a slide groove 41 is provided on the top side wall of the corresponding first half cover 4. The slide groove 41 is not opened horizontally or vertically, but is inclined. The specific inclination angle needs to refer to the form of the variable diameter structural section at the bottom of the head cone 7, and the bottom of the slide groove 41 (the side away from the tip of the head cone 7) is a square through groove, so that the connecting piece 21 used later can slide into the slide groove 41. The connecting piece 21 here adopts the form of a sliding nail and a square nut, so the bottom of the slide groove 41 is a square through groove. First, slide the square nut into the slide groove 41, and then install the head cone 7 on the first half cover 4. Thereafter, install the sliding nail so that it passes through the connecting hole 71 and screws with the square nut, thereby completing the connection between the first half cover 4 and the head cone 7; in addition, the specific structure of the variable diameter structural section can be referred 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 variable diameter structure section. Specifically, the shape of the variable diameter structure section is a vertical transition section + an inclined section. Here, the transverse cross-sectional length of the inclined section gradually increases in the direction away from the head cone 7 and close to the inside of the installation space, forming a variable diameter. 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 fastened through the tooling.

[0063] In a preferred embodiment, see Figure 1 and Figure 5The tops of the first half cover 4 and the second half cover 5 are provided with grooves that match the head cone 7 and the separation energy storage spring 22 for installing 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 structure section, and its diameter matches the bottom end face diameter of the variable diameter structure section.

[0064] Specifically, not only the head cone 7 needs to be installed on the top of the first half cover 4 and the second half cover 5, but also a separation energy storage spring 22 needs to be installed to make the first half cover 4 and the second half cover 5 separate more quickly. The variable diameter structure section here will extend into the matching groove opened by the first half cover 4 and the second half cover 5, and a position for the separation energy storage spring 22 will be reserved at the bottom of the variable diameter 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 pin puller 6 no longer fixes the first half cover 4 and the second half cover 5 to the transfer cabin 1, so the entire separation energy storage spring 22 in the compressed state will no longer be constrained, and will also provide driving force for the first half cover 4 and the second half cover 5 to separate.

[0065] Based on the above description of an electromagnetic shield throwing system, it can be seen that the working principle of an electromagnetic shield throwing system of the present application is as follows:

[0066] First, the energy storage part, the first connecting rod part and the second connecting rod part need to be fixed to the transfer cabin 1, and then the first half cover 4 and the head cone 7 are connected by connecting parts such as sliding nails and square nuts, and the separated energy storage spring 22 is placed in the corresponding groove in the first half cover 4, and then the other second half cover 5 is fastened with it using tooling, and finally the bottom of the first half cover 4 and the second half cover 5 can be connected to the transfer cabin 1 through multiple pin pullers 6 to complete the connection between a fairing and the transfer cabin 1.

[0067] Secondly, when the actual separation of the first half-cover 4 and the second half-cover 5 is carried out, the control system of the rocket activates the electromagnet 20 when the fairing separation needs to be completed. After the electromagnet 20 is activated, the preloaded energy storage spring 17 coordinated therewith will quickly release the stored energy and drive the tuning fork link 3 to move. Based on the above 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 and the third transverse link respectively. 14. The fourth transverse link 2 moves (lifts upward). Due to the setting of the cross-sectional length of the fairing body itself, each transverse link will apply thrust to the first half cover 4 and the second half cover 5 when it is lifted upward. Under the thrust, the pin puller 6 no longer constrains the first half cover 4, the second half cover 5 and the transfer cabin 1, and the separation energy storage spring 22 is also released, accelerating the separation of the two half covers from the transfer cabin 1 or from the cabin section and the rocket body. Finally, the first half cover 4, the second half cover 5, the nose cone 7 and the corresponding connecting piece 21 are separated from the transfer cabin 1, completing the release of the fairing.

[0068] The above description is merely a preferred embodiment of the present application and an illustration of the technical principles employed. Those skilled in the art should understand that the scope of the invention herein is not limited to the technical solutions formed by the specific combination of the above-mentioned technical features, but also encompasses other technical solutions formed by any combination of the above-mentioned technical features or their equivalents without departing from the inventive concept. For example, a technical solution formed by replacing the above-mentioned features with (but not limited to) technical features having similar functions disclosed in this application.

Claims

1. An electromagnetic shield throwing system, characterized in that: The electromagnetic shield ejection system is connected to the cabin section and the rocket body via a transfer cabin (1); the electromagnetic shield ejection system comprises: two separable half shields, which form an installation space when the two half shields are buckled together; 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 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 respectively abut against the same half cover, and the first connecting rod part and the second connecting rod part are connected by transmission 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 abutting 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 nose cone (7), and the nose 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 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 discs (9) via joint supports (10).

4. The electromagnetic shield throwing system according to claim 3, 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 thereof is hinged to one end of the second transverse link (12) and the two bifurcated ends of the tuning fork link (3) via a first shaft pin; A first transverse tensioning support (13), wherein the first transverse tensioning support (13) is movably connected to an end of the second transverse link (12) away from the first transverse link (11); and a 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).

5. The electromagnetic shield throwing system according to claim 3, characterized in that: The second link portion comprises: two mutually cooperating third transverse links (14) and a fourth transverse link (2), one end of the third transverse link (14) being movably connected to the joint support (10), and the other end thereof being 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 via a second axle pin; the end of the fourth transverse link (2) away from the third transverse link (14) being movably connected to a second transverse tensioning support (15); The third transverse link (14) and the fourth transverse link (2) extend between the corresponding two forked ends toward 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 portion 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 portion, and the middle portion of the other end of the first longitudinal connecting rod (16) having a first receiving groove with an opening toward the bottom of the installation space, and a connecting column (161) being provided in the middle portion 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 has a second receiving groove with an opening toward the top of the installation space, an electromagnet (20) is provided in the second receiving groove, and a through hole is 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-reducing structural section. The diameter-reducing 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 realize 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 after the two are buckled together gradually increases along the direction from the nose cone (7) to the transfer cabin (1).

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