CN114636004B

CN114636004B - High-temperature fuel product energy management device and spray pipe

Info

Publication number: CN114636004B
Application number: CN202210541655.4A
Authority: CN
Inventors: 强洪夫; 戴陈超; 王学仁; 刘春波; 任加万; 杨艳丽; 王哲君
Original assignee: Jiangsu Shenlan Aerospace Co ltd; Rocket Force University of Engineering of PLA
Current assignee: Jiangsu Shenlan Aerospace Co ltd; Rocket Force University of Engineering of PLA
Priority date: 2022-05-19
Filing date: 2022-05-19
Publication date: 2022-08-26
Anticipated expiration: 2042-05-19
Also published as: CN114636004A

Abstract

The embodiment of the invention discloses a high-temperature fuel product energy management device and a spray pipe, and relates to the technical field of attitude and orbit control engines. The high-temperature fuel product energy management device comprises a valve core, a rotating shaft mechanism and a driving unit. Wherein, pivot mechanism includes connecting piece and thermal-insulated subassembly. The connecting piece is connected with the valve core. The driving unit is connected with the connecting piece through the heat insulation assembly. So can avoid being in the case and the connecting piece direct and the drive unit of high temperature zone and be connected through the setting of thermal-insulated subassembly, influence drive unit's job stabilization nature. The driving unit can directly drive the valve core through the rotating shaft mechanism so as to realize the rapid switching of the thrust, avoid the response delay caused by indirectly controlling the valve core by utilizing the pressure difference, shorten the response time of the thrust switching and improve the integration degree of the solid attitude control engine.

Description

High-temperature fuel product energy management device and spray pipe

Technical Field

The invention relates to the technical field of attitude and orbit control engines, in particular to a high-temperature fuel product energy management device and a spray pipe.

Background

The intellectualization of the carrier rocket is an important direction for the development of commercial aerospace, but the intellectualization puts higher requirements on the autonomous control capability of the carrier rocket, particularly the requirements on the attitude and orbit control capability of the carrier rocket, and simultaneously, in consideration of the problem of the carrying capacity of the rocket, an attitude and orbit control engine which is light in weight, quick in response and high in integration level is required to provide thrust required by orbit change and attitude adjustment for the carrier rocket.

The attitude and orbit jets are arranged radially or substantially radially with respect to the rocket motor main axis to effect lateral or "turning" motion of the upper stage or recovery section motor of the rocket. Typically, the attitude is provided in pairs, two or more, typically four, with the jets of each pair being disposed opposite each other on either side of the upper stage or recovery section engine casing of the rocket. The orbiting engine nozzle is typically arranged in a cruciform arrangement around the axial direction of the upper stage or recovery section engine, typically at the axial centre of gravity of the rocket engine. The attitude control engine is typically located at the head of the upper stage tail or recovery section engine, i.e., the section away from the center of gravity, to provide maximum torque.

The current carrier rocket carries a liquid attitude and orbit control engine, and the starting and stopping of each spray pipe are realized by controlling the fuel delivery of a pipeline. The liquid attitude and orbit control engine can meet the requirement of quick thrust response, but the liquid attitude and orbit control engine has a complex structure and is difficult to maintain. In contrast, the solid attitude and orbit control engine has the advantages of simple structure, easiness in maintenance and the like.

Compared with a liquid attitude and orbit control engine, a solid attitude and orbit control engine has a certain short plate in the thrust control aspect at present, and the currently adopted solution is to design a hot gas switching component (such as a valve component) to shunt and regulate high-temperature and high-pressure gas generated by the solid attitude and orbit control engine, wherein the switching component is also called as a high-temperature gas energy management device. One common energy management device is to switch the spool between the two nozzles by a solenoid valve, so as to switch the thrust between the different nozzles. However, the traditional energy management device has certain disadvantages, because the gas is high-temperature and high-pressure gas, in order to realize the switching of the valve core between different spray pipes, small gas cavities are generally designed at the left-right symmetrical positions of the valve core, and the electromagnetic valve is used for controlling the opening and closing of the small gas cavities, so that the switching of the position of the valve core is realized by using the pressure difference of the gas.

Disclosure of Invention

Therefore, a high-temperature fuel product energy management device and a spray pipe are needed to be provided, and the technical problem that the thrust switching response of the existing solid attitude and orbit control engine is slow is solved.

In order to solve the technical problems, the first technical scheme adopted by the invention is as follows:

a high temperature fuel product energy management device, comprising:

a valve core;

the rotating shaft mechanism comprises a connecting piece and a heat insulation assembly, and the connecting piece is connected with the valve core; and the driving unit is connected with the connecting piece through the heat insulation assembly so as to drive the valve core.

In some embodiments of the device for energy management of high temperature fuel products, the connecting member is provided with a groove along the axial direction thereof, and the heat insulation assembly is partially filled in the groove and connected with the connecting member.

In some embodiments of the device for energy management of high temperature fuel products, the connecting member includes a body and a connecting portion, the body is connected to the valve element, the body and the connecting portion are connected in an axial direction of the connecting member, the groove is formed in the connecting portion, and a radial dimension of the groove with respect to the connecting member is larger than a radial dimension of the body with respect to the connecting member.

In some embodiments of the device for managing energy of a high-temperature fuel product, the heat insulation assembly includes a first heat insulation member, a hollow member and a second heat insulation member, the first heat insulation member is accommodated in the groove and attached to the groove bottom of the groove, the first heat insulation member can be filled in the groove portion along the axial direction of the connecting member, the hollow member is provided with a hollow cavity, the hollow cavity is penetrated through by the hollow member along the axial direction of the connecting member, the hollow member is inserted in the groove and abutted to the first heat insulation member, and the second heat insulation member is filled in the hollow cavity and connected to the driving unit.

In some embodiments of the high temperature fuel product energy management device, an end of the second thermal shield remote from the first thermal shield is provided with a cut-out having a small end and a large end, the small end and the large end being disposed along an axial direction of the connector, and the small end facing the first thermal shield, and the cut-out is filled with a thermal insulation material.

In some embodiments of the high temperature fuel product energy management device, the second thermal insulation element is provided with a receiving groove, the cut and the receiving groove are arranged along an axial direction of the connecting element, the receiving groove is communicated with the large end portion, and the receiving groove is filled with a thermal insulation material.

In some embodiments of the device for energy management of a high temperature fuel product, the shaft mechanism further comprises a transmission member, the second heat insulating member is provided with a mounting groove, the notch, the accommodating groove and the mounting groove are arranged along an axial direction of the connecting member, the accommodating groove is communicated with the mounting groove, the transmission member partially fills the mounting groove to be connected with the second heat insulating member, and the transmission member is connected between the driving unit and the second heat insulating member.

In some embodiments of the high temperature fuel product energy management device, the outer wall of the hollow member is stepped and has a first shoulder abutting on one end of the connecting portion away from the body, the hollow cavity is stepped and is capable of forming a hole shoulder on the hollow member, the second heat insulating member is stepped and has a second shoulder abutting on the hole shoulder, the second heat insulating member includes a small end section and a large end section which are located on two sides of the second shoulder, the small end section abuts on the first heat insulating member, and the large end section is connected with the driving unit.

In order to solve the technical problems, the invention adopts the following technical scheme:

a spout, comprising:

a housing;

the heat insulation layer group is accommodated in the shell and is surrounded to form a high-temperature cavity;

in the high-temperature fuel product energy management device, the valve core is accommodated in the high-temperature cavity; and the nozzle assembly is arranged on the shell and extends to the high-temperature cavity, and the driving unit drives the valve core so as to control the high-temperature cavity and the nozzle assembly to be communicated and closed.

In some embodiments of the nozzle assembly, the nozzle assembly includes a tail section, a middle section, a head section and a screw, the tail section is exposed from the housing, the middle section is inserted into the tail section, the screw is sleeved on the tail section and the middle section and is respectively in threaded connection with the tail section and the middle section, one end of the head section is inserted into the middle section, the other end of the head section is inserted into the heat insulation layer group to be located in the high temperature cavity, the valve core is of a hollow structure and has a notch, and the driving unit drives the valve core to control the notch to communicate the high temperature cavity with the nozzle assembly.

The embodiment of the invention has the following beneficial effects:

the high-temperature fuel product energy management device is applied to the spray pipe, the spray pipe is guaranteed to have excellent thrust efficiency, the thrust switching speed of the spray pipe and the integration level of a solid attitude and orbit control engine structure can be improved, meanwhile, high temperature generated by fuel products is prevented from being specially transmitted to the driving unit in the thrust switching control process, and normal work of the driving unit is guaranteed. Specifically, the high-temperature fuel product energy management device comprises a valve core, a rotating shaft mechanism and a driving unit. Wherein, pivot mechanism includes connecting piece and thermal-insulated subassembly. The connecting piece is connected with the valve core. The driving unit is connected with the connecting piece through the heat insulation assembly. So can avoid being in the case and the connecting piece direct and the drive unit of high temperature zone and be connected through the setting of thermal-insulated subassembly, influence drive unit's job stabilization nature. The driving unit can directly drive the valve core through the rotating shaft mechanism so as to realize the rapid switching of the thrust, avoid the response delay caused by indirectly controlling the valve core by utilizing the pressure difference, shorten the response time of the thrust switching and improve the integration degree of the solid attitude control engine.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.

Wherein:

FIG. 1 is a schematic view of a nozzle in one embodiment;

FIG. 2 is a sectional view taken along line A-A of FIG. 1;

FIG. 3 is an enlarged view of the portion B of FIG. 2;

FIG. 4 is a schematic view of the spout of FIG. 1 from another perspective;

fig. 5 is a sectional view taken along line C-C in fig. 4.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without inventive step based on the embodiments of the present invention, are within the scope of protection of the present invention.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

In the description of the present invention, it should be noted that if the terms "upper", "lower", "inside", "outside", etc. indicate an orientation or a positional relationship based on that shown in the drawings or that the product of the present invention is used as it is, this is only for convenience of description and simplification of the description, and it does not indicate or imply that the device or the element referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the present invention.

Furthermore, the appearances of the terms "first," "second," and the like, if any, are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.

It should be noted that the features of the embodiments of the present invention may be combined with each other without conflict.

The attitude and orbital jets are arranged radially or substantially radially relative to the rocket motor main axis to effect lateral or "turning" motion of the upper stage or recovery section motor of the rocket. Typically, the attitude is provided in pairs, two or more, typically four, with the jets of each pair being disposed opposite each other on either side of the upper stage or recovery section engine casing of the rocket. The orbiting engine nozzle is typically arranged in a cruciform arrangement around the axial direction of the upper stage or recovery section engine, typically at the axial centre of gravity of the rocket engine. The attitude control engine is typically located at the head of the upper stage tail or recovery section engine, i.e., the section away from the center of gravity, to provide maximum torque.

The current carrier rocket carries a liquid attitude orbit control engine, and the starting and stopping of each spray pipe are realized by controlling the fuel delivery of a pipeline. The liquid attitude and orbit control engine can meet the requirement of quick thrust response, but the liquid attitude and orbit control engine has a complex structure and is difficult to maintain. In contrast, the solid attitude and orbit control engine has the advantages of simple structure, easiness in maintenance and the like.

Compared with a liquid attitude and orbit control engine, the current solid attitude and orbit control engine has a certain short plate in the thrust control aspect, and the currently adopted solution is to shunt and regulate high-temperature and high-pressure fuel gas generated by the solid attitude and orbit control engine by designing a hot gas switching component (such as a valve component), wherein the switching component is also called as a high-temperature fuel gas energy management device. One common energy management device is to switch the spool between the two nozzles by a solenoid valve, so as to switch the thrust between the different nozzles. However, the traditional energy management device has certain disadvantages, because the gas is high-temperature and high-pressure gas, in order to realize the switching of the valve core between different spray pipes, small gas cavities are generally designed at the left-right symmetrical positions of the valve core, and the electromagnetic valve is used for controlling the opening and closing of the small gas cavities, so that the switching of the position of the valve core is realized by using the pressure difference of the gas.

The invention provides a high-temperature fuel product energy management device and a spray pipe for solving the technical problems. In the present embodiment, the high-temperature fuel product energy management device and the nozzle are used for a solid attitude control engine and mounted on a launch vehicle. Specifically, for a non-recovery launch vehicle, the upper stage of the payload generally needs to be equipped with an attitude and orbit control engine, so as to ensure that the attitude of the upper stage is stable after the first stage is separated and the payload carried by the upper stage can be accurately tracked according to the preset requirement. For the recoverable carrier rocket, the attitude of the first-stage recovery section engine can be controlled by the grid rudder in the recovery process, but the use of the grid rudder limits the height of the engine, and after the first-stage engine is separated from the upper stage, the height of the recovery section engine cannot use the grid rudder, so that the attitude and track control engine still needs to be carried to ensure that the first-stage engine can reenter according to the preset attitude. Thus, the hot fuel product energy management device and nozzle in this embodiment are primarily located on the upper stage of the non-recovery launch vehicle and on the first stage of the recovery launch vehicle.

Referring to fig. 1, 2, 4 and 5, the present invention will now be described. The lance includes an outer shell 10, a thermally insulating blanket set 20, a high temperature fuel product energy management device 30 and a nozzle assembly 40. The heat insulation layer group 20 is accommodated in the housing 10. The insulation layer group 20 is surrounded to form a high temperature cavity 100. The housing 10 is provided with an inlet pipe 50 for the fuel product to the high temperature chamber 100. In this example, the fuel product is a high temperature combustion gas. It is understood that in other embodiments, the fuel product may also be steam, a gas-liquid mixture, or a gas-solid mixture. Further, the high-temperature fuel product energy management device 30 includes a valve element 31, a rotating shaft mechanism 32, and a driving unit 33. The spindle mechanism 32 includes a connector 321 and a heat shield assembly 322. The connection member 321 is connected to the spool 31. The driving unit 33 is connected to the connection member 321 through the adiabatic assembly 322 to drive the valve cartridge 31. Further, the valve body 31 is housed in the high temperature chamber 100. The nozzle assembly 40 is disposed in the housing 10 and extends to the high temperature chamber 100, and the driving unit 33 drives the valve plug 31 to control the communication and closing of the high temperature chamber 100 and the nozzle assembly 40. The fuel product may be ejected from the nozzle tube through the nozzle assembly 40 in communication with the high temperature chamber 100 to provide thrust after entering the high temperature chamber 100 through the inlet tube 50.

In summary, the embodiment of the invention has the following beneficial effects: the high-temperature fuel product energy management device 30 of the above-mentioned scheme is applied and equipped in the nozzle, and besides ensuring that the nozzle has excellent thrust performance, it can also enhance the nozzle thrust switching rate and the integration level of the solid attitude and orbit control engine structure, and meanwhile, it prevents the high temperature generated by the fuel product from being specially transmitted to the driving unit 33 in the process of controlling thrust switching, and ensures the normal operation of the driving unit 33. Specifically, the high-temperature fuel product energy management device 30 includes a valve body 31, a rotating shaft mechanism 32, and a driving unit 33. Wherein, the shaft mechanism 32 includes a connecting member 321 and a heat insulation assembly 322. The connector 321 is connected to the spool 31. Drive unit 33 is coupled to coupling member 321 by an insulation assembly 322. Due to the arrangement of the heat insulation assembly 322, the valve core 31 and the connecting piece 321 in the high temperature region can be prevented from being directly connected with the driving unit 33, and the working stability of the driving unit 33 can be prevented from being influenced. The driving unit 33 can directly drive the valve core 31 through the rotating shaft mechanism 32 to realize the rapid switching of the thrust, avoid the response delay caused by indirectly controlling the valve core 31 by using the pressure difference, shorten the response time of the thrust switching, and improve the integration degree of the solid attitude control engine.

As shown in fig. 1 and 4, in the present embodiment, the number of the nozzle assemblies 40 is two and the nozzle assemblies are arranged at a certain angle. The driving unit 33 can drive the valve core 31 to realize communication of different nozzle assemblies 40 with the high temperature chamber 100 respectively or simultaneously to realize switching of the thrust direction. It is understood that in other embodiments, the number of the nozzle assemblies 40 may be one, and the driving unit 33 can drive the valve core 31 to realize the communication and the closing of the nozzle assemblies 40 with the high temperature chamber 100, and realize the switching of the thrust. In the above embodiment, the thrust direction of the spacecraft may be switched by providing a plurality of nozzles and switching the presence or absence of thrust of each nozzle. In other embodiments, the number of the nozzle assemblies 40 may be two or more, and the valve core 31 is driven by the driving unit 33 to realize that different nozzle assemblies 40 are respectively or simultaneously communicated with the high temperature chamber 100 to form a combination of multiple thrust directions. Further, the manner in which the driving unit 33 drives the valve element 31 includes moving or rotating. In the present embodiment, the driving unit 33 can drive the valve body 31 to rotate to realize the switching of the thrust. It will be appreciated that in other embodiments, the drive unit 33 may drive the spool 31 to move to effect the switching of the thrust. That is, the nozzle assembly 40 is communicated with and closed off from the high temperature chamber 100 by the movement of the valve core 31, and the fuel product is divided and regulated. In this embodiment, the valve core 31 and the connecting member 321 may be made of high temperature alloy, such as rhenium, tungsten alloy, molybdenum alloy, or ceramic-based high temperature resistant material.

In one embodiment, as shown in FIG. 3, the connector 321 is recessed with a groove 200 along its axial direction. Insulation assembly 322 partially fills recess 200 and is connected to connector 321. The connection area between the connecting member 321 and the heat insulation assembly 322 can be increased by the arrangement of the groove 200, and the connection stability between the connecting member 321 and the heat insulation assembly 322 is further increased. The heat insulation assembly 322 is partially filled in the groove 200, so that only part of the heat insulation assembly 322 is in direct contact with the connecting member 321, and the driving unit 33 can be disposed at an end of the heat insulation assembly 322 away from the groove 200, so that the connecting member 321 can be effectively isolated by the heat insulation assembly 322, and heat on the connecting member 321 is prevented from being transferred to the driving unit 33 while connection stability is ensured.

In one embodiment, referring to fig. 2 and 3, the connecting member 321 includes a body 3211 and a connecting portion 3212. The body 3211 is connected to the spool 31. The body 3211 and the connection portion 3212 are connected in the axial direction of the connection member 321. This enables the connection portion 3212 to move away from the high temperature chamber 100 in the axial direction of the connection member 321, and reduces the temperature of the high temperature chamber 100 transferred to the connection portion 3212. The groove 200 is formed in the connecting portion 3212, and a radial dimension of the groove 200 with respect to the connecting member 321 is larger than a radial dimension of the body 3211 with respect to the connecting member 321. Since the heat insulation assembly 322 is partially filled in the groove 200, the heat insulation assembly 322 has a larger radial size relative to the connecting member 321 than the body 3211, which helps to block the radiant heat transmitted from the body 3211 and further reduce the temperature transmitted to the driving unit 33. Meanwhile, the radial dimension of the groove 200 relative to the connecting piece 321 is larger than the radial dimension of the body 3211 relative to the connecting piece 321, so that the connecting portion 3212 has a larger radial dimension than the body 3211, thereby avoiding the rigidity of the connecting piece 321 reduced due to the opening of the groove 200, improving the connection stability between the valve element 31 and the driving unit 33, and improving the ability of the connecting piece 321 to resist thermal deformation.

In one embodiment, as shown in fig. 3, the insulation assembly 322 includes a first insulation 3221, a hollow member 3222, and a second insulation 3223. The first thermal insulation member 3221 is accommodated in the groove 200 and attached to the bottom of the groove 200. The first insulation member 3221 can partially fill the groove 200 in the axial direction of the connection member 321. The heat transferred from the bottom of the groove 200 can be reduced by the arrangement of the first thermal insulation member 3221, and the heat directly transferred or radiatively transferred to the bottom of the groove 200 by the body 3211 can be reduced. The first heat insulation member 3221 may be made of a high temperature resistant alloy having low thermal conductivity and high strength. Further, the hollow member 3222 is provided with a hollow cavity 300. The hollow cavity 300 penetrates the hollow member 3222 in an axial direction of the connection member 321. The hollow member 3222 is inserted into the groove 200 and abuts against the first heat insulating member 3221. Therefore, the connecting area between the hollow member 3222 and the connecting portion 3212 can be increased, and the connecting stability of the hollow member 3222 and the connecting portion 3212 can be improved. Further, a second heat insulator 3223 is filled in the hollow cavity 300 and connected to the driving unit 33. The second thermal insulation member 3223 may be made of other high temperature alloy such as niobium alloy. This allows a part of the heat on the connecting member 321 to be transmitted to the driving unit 33 through the attenuation of the first and

second heat insulators

3221 and 3223 in sequence in the axial direction of the connecting member 321. A part of the heat on the connection member 321 is transferred to the driving unit 33 through the attenuation of the first insulation member 3221, the hollow member 3222 and the second insulation member 3223 in sequence. The remaining heat on the connection member 321 is transferred to the driving unit 33 through the attenuation of the hollow member 3222 and the second insulation member 3223 in sequence.

In one embodiment, with continued reference to fig. 3, the end of the second insulation element 3223 away from the first insulation element 3221 is provided with a cut-out 400. The slit 400 has a small end and a large end, which are disposed along the axial direction of the connection member 321, with the small end facing the first thermal insulation member 3221, thereby forming a radial slit. The cut 400 is filled with insulation 3224. This allows the heat of the connecting member 321 to be at least partially attenuated by the heat insulation material 3224 filled in the slit 400 after being transferred to the second heat insulation member 3223, thereby further reducing the temperature of the driving unit 33. In this embodiment, the notch 400 is conical. It is understood that in other embodiments, cutouts 400 may also be in the shape of truncated cones, triangular pyramids, rectangular pyramids, or other slot-like structures having small ends and large ends. Further, the arrangement of the radiation slits and the filling of the heat insulation material 3224 reduce the contact area between the connecting member 321 and the second heat insulation member 3223, thereby further improving the heat insulation effect.

In one embodiment, referring to fig. 3, the second thermal insulation element 3223 is provided with a receiving groove 500. The notch 400 and the receiving groove 500 are provided in the axial direction of the connecting member 321, and the receiving groove 500 communicates with the large end portion. This further extends the dimension of cutout 400 in the axial direction of connecting piece 321. Further, the accommodating groove 500 is filled with a heat insulating material 3224. That is, the volume of the heat insulating material 3224, especially the axial dimension of the heat insulating material 3224 along the connecting member 321, can be further increased by the above arrangement, so that the heat transferred to the driving unit 33 is further attenuated, and the temperature of the driving unit 33 is reduced.

In one embodiment, with continued reference to fig. 3, the shaft mechanism 32 further includes a transmission member 323. The second insulation member 3223 is provided with a mounting groove 600, and the notch 400, the receiving groove 500 and the mounting groove 600 are disposed in an axial direction of the connection member 321. The receiving groove 500 communicates with the mounting groove 600. The transmission member 323 partially fills the mounting groove 600 to be connected with the second adiabatic member 3223. The connection area between the transmission member 323 and the second heat insulation member 3223 can be increased by the installation of the installation groove 600, and the connection stability between the transmission member 323 and the second heat insulation member 3223 is improved. In this embodiment, the mounting groove 600 has a larger radial dimension than the insulation material 3224. It is understood that in other embodiments, the mounting groove 600 may be directly formed on the insulation material 3224. Further, the receiving groove 500 is communicated with the mounting groove 600 so that the insulation material 3224 can directly contact the transmission member 323, and heat is transmitted to the transmission member 323 after being attenuated by the insulation material 3224. Further, the transmission member 323 is connected between the driving unit 33 and the second insulation member 3223. This enables the transmission member 323 to further raise the distance between the driving unit 33 and the high temperature chamber 100, and further lower the temperature of the driving unit 33 while ensuring the transmission. In this embodiment, the transmission member 323 can be made of a titanium alloy with a low thermal conductivity. The transmission member 323 is connected to the second thermal insulation member 3223 by welding. In this embodiment, the transmission member 323 is disposed in the mounting groove 600 to cover the accommodating groove 500, such that the heat insulation material 3224 may have a rigid structure, or a loose multi-particle structure, and each particle may be made of one or more materials. In addition, the insulation material 3224 may also be a mixed structure of particles and powder or liquid to adjust the insulation properties of the insulation material 3224. In this embodiment, the driving unit 33 is a high-speed stepping motor, and drives the rotating shaft mechanism 32 to rotate by controlling the high-speed stepping motor, and finally drives the valve element 31 to rotate. According to the characteristics of the high-speed stepping motor, the forward rotation, the reverse rotation and the rotation angle of the valve core 31 can be controlled, so that the thrust can be rapidly switched.

In one embodiment, with continued reference to fig. 3, the outer wall of the hollow member 3222 is stepped and has a first shoulder 32221. The first shoulder 32221 abuts on an end of the connecting portion 3212 away from the body 3211, so that the first shoulder 32221 and the connecting portion 3212 cooperate to achieve axial positioning of the hollow member 3222, and at the same time, heat propagating in the axial direction of the connecting portion 3212 along the connecting member 321 can pass through the hollow member 3222, thereby attenuating the hollow member 3222. Further, the hollow cavity 300 is stepped and can form a shoulder on the hollow member 3222. The second thermal insulation element 3223 is stepped and has a second shoulder 32231, and the second shoulder 32231 abuts against the hole shoulder to axially position the second thermal insulation element 3223. Further, the second thermal insulation member 3223 includes a small end section and a large end section located at both sides of the second shoulder 32231, the small end section abuts against the first thermal insulation member 3221, the large end section is connected with the driving unit 33, and the accommodating groove 500 is formed at the large end section. By thus connecting the large end section with the driving unit 33, the rigidity of the connection position of the second thermal insulation member 3223 with the driving unit 33 is improved, and the connection stability is improved. Thus, based on the above-mentioned series of embodiments, the heat insulation assembly 322 can form a multi-layer heat attenuation structure to attenuate the heat transferred to the transmission member 323, so as to reduce the temperature of the driving unit 33 and improve the working stability of the driving unit 33. In this embodiment, the connection portion 3212, the hollow member 3222 and the second thermal insulation member 3223 may be connected to each other by a pin 60.

In one embodiment, referring to fig. 2, 3 and 5, the thermal insulation layer set 20 includes at least a first thermal insulation layer 21 attached to the outer shell 10 and a second thermal insulation layer 22 surrounding the high temperature chamber 100, so as to reduce the amount of heat transferred from the high temperature chamber 100 to the outer shell 10. In this embodiment, the second heat insulating layer 22 includes a first heat insulating portion 221 and a second heat insulating portion 222, the first heat insulating portion 221 is provided with a first bearing 70, and the connecting member 321 is inserted into the valve element 31 and connected to the first bearing 70. The second heat insulation portion 222 is provided with a second bearing 80, and the transmission member 323 is inserted into the second bearing 80 and connected to the driving unit 33. Since the first bearing 70 is close to the high temperature chamber 100, it may be made of graphite to improve the high temperature resistance of the first bearing 70. The second bearing 80, which is located away from the high temperature chamber 100 and connected to the transmission member 323, may be a conventional ball bearing to reduce the overall cost of the nozzle. Further, the first adiabatic part 221 and the second adiabatic part 222 are located at both sides of the high temperature chamber 100. The side of the second insulating portion 222 remote from the high temperature chamber 100 is open to facilitate installation of the insulating assembly 322 with the connecting portion 3212. Two outer graphite rings 91 and two inner graphite rings 92 are arranged between the heat insulation assembly 322 and the second heat insulation part 222 and between the connecting part 3212 and the second heat insulation part 222, the two outer graphite rings 91 are arranged at intervals and attached to the second heat insulation part 222, and the two inner graphite rings 92 are clamped between the two outer graphite rings 91 and respectively attached to the heat insulation assembly 322 and the connecting part 3212, so that the two outer graphite rings 91 and the two inner graphite rings 92 can form a labyrinth-type sealing structure. Thus, while ensuring the transmission stability of the heat insulation assembly 322 and the connecting member 321, the airtightness between the heat insulation assembly 322 and the connecting member 321 and the second heat insulation part 222 is ensured, and the leakage of the fuel product is avoided. Further, the side of the first insulating layer 21 away from the high temperature chamber 100 is open, and the corresponding housing 10 is a split structure and includes a housing 11 and an end cap assembly 12. The end cap assembly 12 is capable of capping the housing 11 to seal the side of the first insulating layer 21 remote from the high temperature chamber 100. The end cap assembly 12 includes a first sealing cap 121, a second sealing cap 122 and a flange 123, the first sealing cap 121 and the second sealing cap 122 are inserted into the first heat insulating layer 21 and abut against the second heat insulating layer 222, the second bearing 80 is connected to the second heat insulating layer 222 through the first sealing cap 121 and the second sealing cap 122, and the flange 123 is connected to the housing 11 and abuts against the first heat insulating layer 21 and abuts against the first sealing cap 121 and the second sealing cap 122 against the second heat insulating layer 222, so that the airtightness of the casing 10 can be improved and leakage of fuel products from the casing 10 can be prevented. Further, the flange 123 is provided with an extension portion to form a sleeve structure for accommodating the transmission member 323, so as to further improve the transmission stability of the transmission member 323, and the transmission member 323 and the extension portion are provided with a sealing member 93 to improve the air tightness.

In one embodiment, referring to fig. 2 and 5, the nozzle assembly 40 includes an end section 41, a middle section 42, a head section 43, and a threaded member 44, the end section 41 being exposed from the housing 10. The tail section 41 is radially flared. Further, the middle section 42 is inserted into the end section 41. The screw 44 is sleeved on the tail section 41 and the middle section 42 and is respectively in threaded connection with the tail section 41 and the middle section 42. This enables the screw 44 to secure the connection stability of the tail section 41 and the middle section 42 while promoting the airtightness of the tail section 41 and the middle section 42 from the outside of the tail section 41 and the middle section 42. In this embodiment, the screw 44 is filled in the gap between the casing 11 and the first insulating layer 21 and the end section 41 and the middle section 42, so as to ensure the air tightness in the gap, and meanwhile, the screw 44 can be supported by the casing 11 to ensure the position of the nozzle assembly 40 to be stable, and avoid moving relative to the casing 10 when thrust is generated. Further, one end of the head section 43 is inserted into the middle section 42, and the other end of the head section 43 penetrates through the insulation layer group 20 to be located in the high temperature cavity 100. The head section 43 is provided with a clamping portion 431 clamped between the middle section 42 and the first insulating portion 221 to improve the connection stability between the head section 43 and the middle section 42. The head section 43, the middle section 42 and the tail section 41 are sequentially communicated and the calibers are sequentially increased. Further, the valve core 31 is a hollow structure and has a notch 700. The driving unit 33 drives the valve plug 31 to control the gap 700 to communicate the high temperature chamber 100 with the nozzle assembly 40. Specifically, the valve core 31 is a strand-shaped hollow structure, and the number of the notches 700 is multiple, so as to facilitate the fuel product to enter and exit the valve core 31, reduce the pressure of the fuel product on the valve core 31 while reducing the weight of the valve core 31, thereby reducing the motion resistance of the valve core 31 and improving the sensitivity of thrust switching.

The technical features of the embodiments described above may be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the embodiments described above are not described, but should be considered as being within the scope of the present specification as long as there is no contradiction between the combinations of the technical features.

While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.

Claims

1. A high temperature fuel product energy management device, comprising:

a valve core;

the rotating shaft mechanism comprises a connecting piece and a heat insulation assembly, and the connecting piece is connected with the valve core; and

the driving unit is connected with the connecting piece through the heat insulation assembly to drive the valve core;

the connecting piece is provided with a groove along the axial direction, and the heat insulation assembly is partially filled in the groove and is connected with the connecting piece;

the heat insulation assembly comprises a first heat insulation piece, a hollow piece and a second heat insulation piece, the first heat insulation piece is contained in the groove and attached to the bottom of the groove, the groove can be filled with the first heat insulation piece along the axial direction of the connecting piece, the hollow piece is provided with a hollow cavity, the hollow cavity penetrates through the hollow piece along the axial direction of the connecting piece, the hollow piece is inserted into the groove and abutted against the first heat insulation piece, and the second heat insulation piece is filled in the hollow cavity and connected with the driving unit;

one end, far away from the first heat insulation piece, of the second heat insulation piece is provided with a notch, the notch is provided with a small end portion and a large end portion, the small end portion and the large end portion are arranged along the axial direction of the connecting piece, the small end portion faces the first heat insulation piece, and heat insulation materials are filled in the notch.

2. The high temperature fuel product energy management device of claim 1, wherein the connector comprises a body and a connection portion, the body is connected to the valve element, the body and the connection portion are connected in an axial direction of the connector, the groove is formed in the connection portion, and a radial dimension of the groove with respect to the connector is larger than a radial dimension of the body with respect to the connector.

3. A high temperature fuel product energy management device as claimed in claim 1, wherein the second insulation element is provided with a receiving groove, the cut and the receiving groove are arranged along an axial direction of the connecting element, the receiving groove communicates with the large end portion, and the receiving groove is filled with an insulation material.

4. A high temperature fuel product energy management device as claimed in claim 3, wherein the shaft mechanism further comprises a transmission member, the second heat insulating member is provided with a mounting groove, the cut-out, the receiving groove and the mounting groove are arranged along an axial direction of the connecting member, the receiving groove is communicated with the mounting groove, the transmission member partially fills the mounting groove to be connected with the second heat insulating member, and the transmission member is connected between the driving unit and the second heat insulating member.

5. A high temperature fuel product energy management device as claimed in claim 2, wherein the outer wall of the hollow member is stepped and has a first shoulder abutting against an end of the connecting portion remote from the body, the hollow cavity is stepped and is capable of forming a shoulder on the hollow member, the second insulation member is stepped and has a second shoulder abutting against the shoulder, the second insulation member includes a small end section abutting against the first insulation member and a large end section on both sides of the second shoulder, and the large end section is connected to the driving unit.

6. A spout, characterized by comprising:

a housing;

the high temperature fuel product energy management device of any one of claims 1 to 5, the valve cartridge being received in the high temperature chamber; and

the nozzle assembly is arranged on the shell and extends to the high-temperature cavity, and the driving unit drives the valve core to control the high-temperature cavity to be communicated with and closed by the nozzle assembly.

7. The nozzle of claim 6, wherein the nozzle assembly includes a tail section, a middle section, a head section, and a screw, the tail section is exposed from the housing, the middle section is inserted into the tail section, the screw is sleeved on the tail section and the middle section and is in threaded connection with the tail section and the middle section, one end of the head section is inserted into the middle section, the other end of the head section is inserted into the heat insulation layer group to be located in the high temperature chamber, the valve core is of a hollow structure and has a notch, and the driving unit drives the valve core to control the notch to communicate the high temperature chamber with the nozzle assembly.