WO2023179343A1 - 一种针栓式喷注器及推力室 - Google Patents

一种针栓式喷注器及推力室 Download PDF

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Publication number
WO2023179343A1
WO2023179343A1 PCT/CN2023/079696 CN2023079696W WO2023179343A1 WO 2023179343 A1 WO2023179343 A1 WO 2023179343A1 CN 2023079696 W CN2023079696 W CN 2023079696W WO 2023179343 A1 WO2023179343 A1 WO 2023179343A1
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WO
WIPO (PCT)
Prior art keywords
propellant
gap
housing
needle
flow channel
Prior art date
Application number
PCT/CN2023/079696
Other languages
English (en)
French (fr)
Inventor
章荣军
王春民
高坤
宋大亮
丰雪平
王化余
刘晓伟
钟博
Original Assignee
西安航天动力研究所
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Application filed by 西安航天动力研究所 filed Critical 西安航天动力研究所
Publication of WO2023179343A1 publication Critical patent/WO2023179343A1/zh

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/52—Injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/30—Use of alternative fuels, e.g. biofuels

Definitions

  • the present application relates to the technical field of injectors, and in particular to a pin type injector and a thrust chamber.
  • variable thrust liquid rocket engines The thrust control of variable thrust liquid rocket engines is achieved by controlling the liquid flow.
  • the pin-bolt injector when selecting an injector for a variable thrust liquid rocket engine, not only has an adjustable injection area, but also has the advantages of simple structure, high operating reliability, and low cost.
  • the adjustment of the moving parts of the needle bolt injector usually adopts mechanical adjustment or hydraulic actuation adjustment.
  • hydraulic actuation adjustment has good adaptability and stable spray combustion efficiency, and is an ideal adjustment solution for needle-bolt injectors.
  • the object of the present invention is to provide a needle bolt injector and a thrust chamber to solve the problem of poor assembly consistency and low operability of the central adjustment component of the needle bolt injector, which affects the needle bolt injector. work reliability issues.
  • the present invention provides a needle plug injector, which includes: a housing, a central cylinder, a center rod and a needle plug.
  • the central cylinder is located in the housing and is fixedly connected to the housing.
  • the needle pin is located between the housing and the central cylinder and can move along the axial direction of the housing.
  • the central rod is located in the central cylinder and is fixedly connected to the central cylinder.
  • the shell is provided with a first cavity and a first propellant flow channel connected with the first cavity.
  • the first propellant When the first propellant enters the first propellant flow channel along the first cavity, the first propellant is Under the action, the needle plug moves along the axial direction of the housing, and the first propellant enters the first gap formed between the needle plug and the housing from the first propellant flow channel, and is ejected along the first gap.
  • the central cylinder is provided with a second cavity and a second propellant flow channel connected with the second cavity.
  • the second propellant enters the second propellant flow channel along the second cavity, the second propellant flows from the center
  • the second gap formed between the rod and the central cylinder is ejected.
  • the center line of the first gap and the center line of the second gap have an intersection point.
  • the central cylinder is located in the housing and is fixedly connected to the housing.
  • the needle pin is located between the housing and the central cylinder and can move along the axial direction of the housing.
  • the central rod is located in the central cylinder and is fixedly connected with the central cylinder. In this way, the relative positions of the central rod, the central cylinder and the housing can be fixed, thereby ensuring that each component is coaxially arranged with the housing, and can prevent the needle bolt injector from being moved when the needle bolt moves along the axial direction of the housing. Relative displacements occur between other components, affecting the consistency of component assembly.
  • the shell is provided with a first cavity and a first propellant flow channel connected with the first cavity.
  • the first propellant When the first propellant enters the first propellant flow channel along the first cavity, the first propellant is Under the action, the needle plug moves along the axial direction of the housing, and the first propellant enters the first gap formed between the needle plug and the housing from the first propellant flow channel, and is ejected along the first gap.
  • the central cylinder is provided with a second cavity and a second propellant flow channel connected with the second cavity.
  • the second propellant enters the second propellant flow channel along the second cavity, the second propellant flows from the center
  • the second gap formed between the rod and the central cylinder is ejected. And the center line of the first gap and the center line of the second gap have an intersection point.
  • the present invention can only adjust the flow rate of the first propellant into the first cavity to change the force of the first propellant on the needle plug, thereby changing the axial movement distance of the needle plug along the housing, so as to achieve the goal of adjusting the first propellant to the first cavity.
  • the needle bolt injector provided by the present invention not only has consistency in component assembly, but also has the advantage of strong operability, which can avoid adverse effects caused by improper operation to a certain extent, thereby improving its Reliability of work.
  • the present invention also provides a thrust chamber, including a combustion chamber, a nozzle assembly and the pin-bolt injector described in the first aspect.
  • the pin-bolt injector is used to inject the first propellant and the second propellant into the combustion chamber, so that the first propellant and the second propellant collide, mix and burn in the combustion chamber.
  • the combustion chamber is used to accommodate the combustion products of the first propellant and the second propellant after impact, mixing and combustion.
  • the nozzle assembly is used to eject the combustion products to generate the thrust required by the thrust chamber.
  • Figure 1 is a schematic cross-sectional view of a pin-type injector provided by an embodiment of the present invention
  • Figure 2 is a partially enlarged schematic diagram of Figure 1.
  • Variable thrust liquid rocket engines have technical advantages in many situations of aerospace transportation and space flight, such as achieving optimal thrust control, improving maneuverability and control flexibility for aircraft rendezvous and docking, improving ballistic maneuverability and improving penetration capabilities, Interstellar soft landing, etc.
  • variable thrust liquid rocket engines The thrust control of variable thrust liquid rocket engines is achieved through flow control. In order to achieve the best spray effect under variable thrust conditions, it is necessary to control the injection conditions while controlling the flow rate.
  • the pin-bolt injector not only has the characteristics of adjustable injection area, but also has the advantages of simple structure, high operating reliability, and low cost. It has become the preferred injector solution in variable thrust liquid rocket engines.
  • the adjustment of the moving parts of the needle bolt injector usually adopts mechanical adjustment (such as motor drive) or hydraulic actuation adjustment (such as hydraulic-spring balance actuation).
  • mechanical adjustment such as motor drive
  • hydraulic actuation adjustment such as hydraulic-spring balance actuation
  • the adaptive adjustable needle bolt injector with hydraulic actuation adjustment has good adaptability and stable spray combustion efficiency, and has the characteristics of compact and simple structure. It is an ideal variable thrust liquid rocket engine needle bolt. Injector adjustment scheme.
  • an embodiment of the present invention provides a needle bolt injector, including: a housing 1, a central cylinder 2, and a central rod 4 and pin plug 3.
  • the central cylinder 2 is located in the housing 1 and is fixedly connected to the housing 1.
  • the needle pin 3 is located between the housing 1 and the central cylinder 2 and can move along the axial direction of the housing 1.
  • the central rod 4 is located in the central cylinder 2 and is fixedly connected to the central cylinder 2 .
  • the housing 1 is provided with a first cavity 11 and a first propellant flow channel connected with the first cavity 11.
  • the central cylinder 2 is provided with a second cavity 21 and a second propellant flow channel 22 connected with the second cavity 21.
  • the second propellant is ejected from the second gap 23 formed between the central rod 4 and the central cylinder 2 .
  • the center line of the first gap 14 and the center line of the second gap 23 have an intersection point.
  • the first propellant needs to be supplied into the first cavity 11.
  • the cavity will be filled and pressure built up in the first propellant flow channel.
  • the needle plug 3 moves upward along the axial direction of the housing 1, thus expanding the size of the first gap 14 so that The first propellant is ejected along the first gap 14 .
  • the second propellant is pushed into the second cavity 21.
  • the second propellant enters the second gap 23 formed by the central cylinder 2 and the central rod 4 along the second propellant flow channel 22, and passes through the second gap 23.
  • the liquid outlet squirts out.
  • the needle bolt 3 moves along the axial direction of the housing 1, the needle bolt 3 is pushed to one end of the central barrel 2 and moves toward the upper end of the housing 1, thereby adjusting the size of the second gap 23. That is, since the liquid outlet of the second gap 23 is partially blocked by the needle plug 3, when the needle plug 3 moves upward along the axial direction of the housing 1, the size of the liquid outlet of the second gap 23 will also be increased simultaneously. , realizing the adjustment of the second propellant injection area. At the intersection of the center line of the first gap 14 and the center line of the second gap 23, the first propellant and the second propellant impact, mix and burn.
  • the central barrel 2 is located in the housing 1 and is fixedly connected to the housing 1 .
  • the needle pin 3 is located between the housing 1 and the central barrel 2 and can move along the axial direction of the housing 1 .
  • the central rod 4 is located in the central cylinder 2 and is fixedly connected to the central cylinder 2 . In this way, the relative positions of the central rod 4, the central cylinder 2 and the housing 1 can be fixed, thereby ensuring that each component is coaxially arranged with the housing 1, and when the needle bolt 3 moves along the axial direction of the housing 1, it can avoid Relative displacement occurs between other components of the needle injector, affecting the consistency of component adjustment.
  • the housing 1 is provided with a first cavity 11 and a first propellant flow channel connected with the first cavity 11.
  • the needle plug 3 moves along the axial direction of the housing 1, and the first propellant enters the first gap 14 formed between the needle plug 3 and the housing 1 from the first propellant flow channel, and moves along the first propellant flow channel.
  • the first gap 14 ejects.
  • the central cylinder 2 is provided with a second cavity 21 and a second propellant flow channel 22 connected with the second cavity 21.
  • the second propellant is ejected from the second gap 23 formed between the central rod 4 and the central cylinder 2 .
  • the center line of the first gap 14 and the center line of the second gap 23 have an intersection point.
  • the embodiment of the present invention can only adjust the flow rate of the first propellant into the first cavity 11 to change the force of the first propellant on the needle plug 3, thereby changing the axial movement of the needle plug 3 along the housing 1 distance to adjust the size of the first gap 14.
  • the needle bolt 3 moves along the axial direction of the housing 1, the needle bolt 3 is pushed to one end of the central barrel 2 and moves toward the upper end of the housing 1, thereby achieving the first Adjusting the size of the second gap 23 will cause corresponding changes in the impact, mixing and combustion efficiency of the first propellant and the second propellant at the intersection point, and the operability will be enhanced.
  • the pin-bolt injector provided by the embodiment of the present invention not only has consistency in component assembly, but also has the advantage of strong operability, and can avoid adverse effects caused by improper operation to a certain extent, thereby Improve the reliability of its work.
  • the central cylinder 2 and the housing 1 are fixedly connected through the pressure ring 7, and the central cylinder 2 is precisely positioned to securely fix the central cylinder 2 to the housing 1.
  • the center rod 4 and the center cylinder 2 are fixedly connected through a self-locking nut 8, and the center rod 4 is precisely positioned to achieve coaxial arrangement of the housing 1, the needle bolt 3, the center cylinder 2 and the center rod 4.
  • a circumferential channel is formed at the connection between the central rod 4 and the central cylinder 2 so that the second propellant in the second cavity 21 can enter the second propellant flow channel 22 along the circumferential channel.
  • first propellant is generally a fuel propellant
  • second propellant is generally an oxidizer propellant, which is not limited in the embodiment of the present invention.
  • the central barrel 2 and the pin plug 3 are usually made of high-temperature alloys, that is, the temperature range meets normal temperature to 800°C, and the linear expansion coefficient of the pin plug 3 material should be higher than that of the central barrel 2 material to avoid temperature rise.
  • the gap between the rear needle plug 3 and the central barrel 2 becomes smaller, causing the needle plug 3 to get stuck, affecting the normal operation of the needle plug injector.
  • the first gap 14 is provided axially along the housing 1
  • the second gap 23 is provided radially along the central cylinder 2 .
  • the first gap 14 is arranged along the axial direction of the housing 1 and is evenly distributed along the circumferential direction of the housing 1, ultimately forming an axially injected outer ring annular gap.
  • the second gap 23 is arranged radially along the central cylinder 2 and evenly distributed along the circumferential direction of the central cylinder 2, ultimately forming an inner ring annular gap for radial injection. Based on this, there must be an intersection point between the two annular center lines, so that the first propellant and the second propellant collide, mix and burn at the intersection point of the two annular gaps, thereby generating the thrust required by the thrust chamber.
  • the first propellant flow channel includes a first sub-flow channel 12 and a second sub-flow channel 13 .
  • the first sub-flow channel 12 is arranged along the axial direction of the housing 1.
  • the liquid inlet of the first sub-flow channel 12 is connected with the first cavity 11, and the liquid outlet is in contact with the first end of the needle plug 3.
  • the needle plug 3 moves along the axial direction of the housing 1 under the action of the first propellant.
  • the second sub-flow channel 13 is arranged along the radial direction of the housing 1.
  • the liquid inlet of the second sub-flow channel 13 is connected to the first cavity 11, and the liquid outlet is connected to the first gap 14.
  • the first propellant enters the first gap 14 from the second sub-flow channel 13 and is ejected along the first gap 14.
  • the first propellant in the first sub-flow channel 12 will generate hydraulic force, and the first sub-flow channel 12
  • the liquid outlet is in contact with the first end of the needle plug 3, and the hydraulic actuating force provides an upward force along the axial direction of the housing 1 to the first end of the needle plug 3, so that the needle plug 3 can be moved under the action of the hydraulic actuating power. , moving upward.
  • the first propellant enters the first cavity 11, it will be injected into the first sub-channel 12 and the second sub-channel 13 respectively along the direction of the liquid outlet of the first cavity 11.
  • the first propellant will also enter the first gap 14 along the second sub-flow channel 13 and finally be ejected from the liquid outlet of the first gap 14 .
  • the volume of the first sub-channel 12 will change accordingly, and the upward movement distance of the needle plug 3 will be correspondingly changed, thereby adjusting the size of the first gap 14, and finally achieving the goal of adjusting the first propellant flow rate. 1. Adjustment of propellant ejection area.
  • the size of the first gap 14 and the size of the liquid outlet of the second gap 23 increase simultaneously.
  • the first end of the needle plug 3 is in contact with the first sub-flow channel 12
  • the second end of the needle plug 3 is also in contact with the liquid outlet of the second gap 23
  • the third end of the needle plug 3 is in contact with the liquid outlet of the second gap 23.
  • the two ends are gradually narrowing structures.
  • the force of the first propellant increases, it means that the force on the upward movement of the needle plug 3 increases, causing the needle plug 3 to move upward along the axial direction of the housing 1, and the first gap 14
  • the size will gradually increase, and at the same time, the second end of the needle plug 3 will also be far away from the liquid outlet of the second gap 23, so that the shielding portion of the liquid outlet of the second gap 23 will gradually decrease, that is, the outlet of the second gap 23 will also increase.
  • the area of the liquid port increases the injection area of the first propellant and the second propellant at the same time, resulting in greater thrust after impact, mixing and combustion.
  • the housing 1 has a first limiting surface 15 , the first limiting surface 15 is located on one side of the liquid outlet of the first sub-flow channel 12 , and the first limiting surface 15 is close to the needle plug 3 The first side of the first end.
  • the central barrel 2 has a second limiting surface 24 , and the second limiting surface 24 is close to the second side of the first end of the needle plug 3 .
  • the first limiting surface 15 and the second limiting surface 24 are used to limit the axial movement distance of the needle bolt 3 .
  • the first limiting surface 15 and the second limiting surface 24 limit the lowest position and the highest position of the movement of the needle plug 3 . It can be understood that when the first end of the needle plug 3 is at the lowest position, that is, when the first end is in contact with the first limiting surface 15, the second end of the needle plug 3 will not completely block the liquid discharge from the second gap 23. port, so that the second propellant can be ejected from the second gap 23. At the same time, the size of the first gap 14 also needs to meet the injection conditions when the pin-bolt injector initially operates.
  • the needle plug 3 When the first end of the needle plug 3 is at the highest position, that is, when the first end is in contact with the second limiting surface 24, the needle plug 3 will not completely separate from the housing 1 and the central tube 2, but is still limited to the housing 1 and the central tube 2. between the central cylinders 2, so that the first gap 14 can stably eject the first propellant, and the injector can still work stably.
  • the first limiting surface 15 can be detachably connected to the housing 1 , or can be integrally formed with the housing 1 .
  • the second limiting surface 24 can also be integrally formed with the central tube 2 or detachably connected with the central tube 2 .
  • the second limiting surface 24 can be a limiting step on the central cylinder 2 , that is, a boss structure as shown in FIG. 1 , which is not specifically limited in this embodiment of the present invention.
  • the needle plug injector further includes an elastic component 5 , and the elastic component 5 is located between the first end of the needle plug 3 and the central barrel 2 .
  • the first end of the elastic component 5 is in contact with the second side of the first end of the needle plug 3
  • the second end of the elastic component 5 is in contact with the other end of the central barrel 2 .
  • the first side of the first end of the needle plug 3 contacts the first limiting surface 15.
  • the needle plug 3 moves to the side away from the first limiting surface 15, and the first end of the needle plug 3 moves to the side away from the first limiting surface 15.
  • the elastic component 5 acts on the first end of the needle plug 3, and the force of the elastic component 5 and the hydraulic force are completely opposite forces.
  • the elastic component 5 will also change the force on the needle plug 3 accordingly, so that the needle plug 3 can act in two ways. Adjustment and positioning can be re-realized under the balance of forces, thereby achieving synchronous adjustment of injection during thrust adjustment and ensuring the stable operation of the needle bolt injector.
  • the elastic component 5 includes a washer 52 and a spring 51, and the thickness of the washer 52 can be adjusted to cause a certain initial compression amount of the spring 51.
  • a linear change in the stiffness of the spring 51 within the adjustment range can be achieved.
  • the spring 51 can also be provided with a pretightening force, thereby preventing the needle bolt 3 from moving during non-working periods and enabling it to withstand flight overload.
  • the central barrel 2 since the central barrel 2 has the second limiting surface 24, it can also prevent the spring 51 from being over-compressed, or when the spring 51 breaks and causes the adjustment of the needle bolt 3 to fail, the needle bolt 3 can be fixed in position, ensuring that the needle bolt can be fixed in position.
  • the injector works stably, further improving its working reliability.
  • the pin-bolt injector also includes an adjustment gasket 6.
  • the adjustment gasket 6 is located between the central cylinder 2 and the housing 1, and is used to adjust the central cylinder 2 and the housing 1. The relative position of the housing 1.
  • the adjustment gasket 6 is used to adjust the relative position of the central cylinder 2 and the housing 1 so that the central cylinder 2 is coaxial with the center of the housing 1 and does not block the liquid outlet of the second gap 23, so that the second gap 23 is not blocked.
  • the size of the liquid outlet of the gap 23 can meet the injection conditions during the initial operation of the pin-bolt injector.
  • the needle injector further includes a first sealing ring 91 and a second sealing ring 92 .
  • the first sealing ring 91 is provided between the needle plug 3 and the housing 1 .
  • the second sealing ring 92 is provided between the inner wall of the needle plug 3 and the outer wall of the central barrel 2 . Based on this, the first sealing ring 91 is located between the first end of the needle plug 3 and the housing 1 for sealing the first propellant in the first sub-flow channel 12 to avoid leakage of the first propellant, thereby causing Adjustment failed.
  • the second sealing ring 92 is located between the inner wall of the needle plug 3 and the outer wall of the central barrel 2 and is used to seal the gas generated when the needle plug injector is operating and to prevent heat from escaping, thereby reducing the first propellant and the second propellant.
  • the propellant combustion efficiency and gas escape will also directly affect the performance of the needle injector, resulting in a reduction in the thrust generated by the engine's thrust chamber.
  • FIG. 1 there is a first fitting gap and a second fitting gap between the inner wall of the needle plug 3 and the outer wall of the central barrel 2 .
  • the first fitting gap is set away from the liquid outlet of the first gap 14, and the size of the first fitting gap is 0.01 mm to 0.02 mm.
  • the second fitting gap is set close to the liquid outlet of the first gap 14, and the size of the second fitting gap is 0.005mm to 0.01mm.
  • the third fitting gap is an annular fitting gap, and the size of the annular fitting gap is 0.005mm to 0.01mm. Specifically, as shown in FIG.
  • the first fitting gap and the second fitting gap are located between the outer wall of the cylindrical section of the central barrel 2 and the inside of the needle plug 3 , and the third fitting gap is provided close to the pressure ring 7 . in this way.
  • This can ensure the flexible movement of the needle plug 3, prevent unnecessary friction between the inner wall of the needle plug 3 and the outer wall of the central barrel 2, and ensure accurate coaxial positioning between the outer wall of the central barrel 2 and the housing 1, and adjust the first push.
  • the needle plug 3 will not be stuck. After the temperature is raised, the needle plug 3 can also be prevented from being stuck, affecting the normal operation of the needle plug injector.
  • embodiments of the present invention provide a thrust chamber, including a combustion chamber, a nozzle assembly and a needle injector.
  • the pin-bolt injector is used to inject the first propellant and the second propellant into the combustion chamber, so that the first propellant and the second propellant collide, mix and burn in the combustion chamber.
  • the combustion chamber is used to accommodate the combustion products of the first propellant and the second propellant after impact, mixing and combustion.
  • the nozzle assembly is used to eject the combustion products to generate the thrust required by the thrust chamber.
  • the beneficial effects of the thrust chamber provided by the second aspect are the same as the beneficial effects of the pin-type injector described in the first aspect or any possible implementation of the first aspect, and will not be described again here.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)

Abstract

一种针栓式喷注器，包括壳体、中心筒、中心杆以及针栓；中心筒位于壳体内，且与壳体固定连接，针栓位于壳体以及中心筒之间，可沿壳体的轴向运动；中心杆位于中心筒内，且与中心筒固定连接；壳体上开设有第一腔体以及与第一腔体相连通的第一推进剂流道，当第一推进剂沿第一腔体进入第一推进剂流道时，在第一推进剂的作用下，针栓沿壳体的轴向运动，第一推进剂从第一推进剂流道进入针栓与壳体之间形成的第一间隙中，并沿第一间隙喷出，用于解决针栓式喷注器的中心组件装配的一致性较差，影响针栓式喷注器的工作可靠性的问题。还公开了一种推力室，包括燃烧室、喷管组件和上述的针栓式喷注器。

Description

[根据细则26改正 24.03.2023]一种针栓式喷注器及推力室
本申请要求于2022年03月21日提交中国专利局、申请号为202210280541.9、申请名称为“一种针栓式喷注器及推力室”的中国专利优先权，其全部内容通过引用结合在本申请中。
技术领域
本申请涉及喷注器技术领域，尤其涉及一种针栓式喷注器以及推力室。
 背景技术
变推力液体火箭发动机的推力控制是通过控制液体流量来实现的。为达到最佳的液体喷雾效果，在选择变推力液体火箭发动机的喷注器时，针栓式喷注器不仅喷注面积可调，还具有结构简单、工作可靠性高、成本低等优点。
针栓式喷注器运动件的调节通常采用机械调节或液压作动调节。其中，液压作动调节具有很好的适应性和稳定的喷雾燃烧效率，是较为理想的针栓式喷注器的调节方案。
但目前液压作动调节的针栓式喷注器的中心调节组件装配的一致性较差，可操作性不高，会影响针栓式喷注器的工作可靠性。
发明内容
本发明的目的在于提供一种针栓式喷注器以及推力室，以解决针栓式喷注器的中心调节组件装配的一致性较差，可操作性不高，影响针栓式喷注器的工作可靠性问题。
为了实现上述目的，第一方面，本发明提供一种针栓式喷注器，包括：壳体、中心筒、中心杆以及针栓。中心筒位于壳体内，且与壳体固定连接，针栓位于壳体以及中心筒之间，可沿壳体的轴向运动。中心杆位于中心筒内，且与中心筒固定连接。壳体上开设有第一腔体以及与第一腔体相连通的第一推进剂流道，当第一推进剂沿第一腔体进入第一推进剂流道时，在第一推进剂的作用下，针栓沿壳体的轴向运动，第一推进剂从第一推进剂流道进入针栓与壳体之间形成的第一间隙中，并沿第一间隙喷出。中心筒上开设有第二腔体以及与第二腔体相连通的第二推进剂流道，当第二推进剂沿第二腔体进入第二推进剂流道时，第二推进剂从中心杆与中心筒之间形成的第二间隙喷出。其中，第一间隙的中心线和第二间隙的中心线具有交点。
采用上述技术方案的情况下，中心筒位于壳体内，且与壳体固定连接，针栓位于壳体以及中心筒之间，可沿壳体的轴向运动。中心杆位于中心筒内，且与中心筒固定连接。如此，能够将中心杆、中心筒以及壳体的相对位置固定，从而保证各零部件与壳体同轴设置，且能够在针栓沿壳体的轴向运动时，避免针栓式喷注器的其他组件之间产生相对位移，影响组件装配的一致性。壳体上开设有第一腔体以及与第一腔体相连通的第一推进剂流道，当第一推进剂沿第一腔体进入第一推进剂流道时，在第一推进剂的作用下，针栓沿壳体的轴向运动，第一推进剂从第一推进剂流道进入针栓与壳体之间形成的第一间隙中，并沿第一间隙喷出。中心筒上开设有第二腔体以及与第二腔体相连通的第二推进剂流道，当第二推进剂沿第二腔体进入第二推进剂流道时，第二推进剂从中心杆与中心筒之间形成的第二间隙喷出。且第一间隙的中心线和第二间隙的中心线具有交点。基于此，本发明可以仅通过调整第一推进剂进入第一腔体的流量，改变第一推进剂对针栓的作用力，从而改变针栓沿壳体的轴向运动距离，以实现对于第一间隙的尺寸的调整，当针栓沿壳体的轴向运动时，针栓推向中心筒的一端，向壳体的上端运动，从而实现第二间隙的尺寸的调整，使得第一推进剂与第二推进剂在交点处撞击、混合和燃烧的效率也会产生相应的改变，可操作性得到增强。由此可见，本发明提供的针栓式喷注器不仅在组件装配方面具有一致性，还具有可操作性较强的优点，能够在一定程度上避免因为操作不当造成的不良影响，从而提高其工作的可靠性。
第二方面，本发明还提供一种推力室，包括燃烧室、喷管组件以及第一方面所述的针栓式喷注器。针栓式喷注器用于将第一路推进剂以及第二路推进剂喷入燃烧室内，以使第一路推进剂以及第二路推进剂在燃烧室内撞击、混合和燃烧。燃烧室用于容纳第一路推进剂以及第二路推进剂撞击、混合和燃烧后的燃烧产物。喷管组件用于将燃烧产物喷出，以产生推力室所需的推力。
第二方面提供的推力室的有益效果与第一方面所述的针栓式喷注器的有益效果相同，此处不做赘述。
 附图说明
为了更清楚地说明本申请实施例或现有技术中的技术方案，下面将对实施例或现有技术描述中所需要使用的附图进行说明：
图1本发明实施例提供的针栓式喷注器的剖面示意图；
图2为图1的局部放大示意图。
附图标记：1-壳体，                               2-中心筒，3-针栓，                               4-中心杆，5-弹性组件，                           6-调整垫片，7-压环，                               8-自锁螺母，11-第一腔体，                          12-第一子流道，13-第二子流道，                        14-第一间隙，15-第一限位面，                        21-第二腔体，22-第二推进剂流道，                    23-第二间隙，24-第二限位面，                        51-弹簧，52-垫环，                              91-第一密封圈，92-第二密封圈。
 具体实施方式
变推力液体火箭发动机在航天运输和空间飞行的许多情况下具有技术上的优越性，如实现最佳推力控制、提高飞行器交会对接的操纵控制灵活性、改善弹道的机动性及提高突防能力、星际软着陆等。
变推力液体火箭发动机的推力控制是通过流量控制实现的。为实现在变推力条件下的最佳喷雾效果，在控制流量的同时还需要对喷注条件进行控制。针栓式喷注器不仅具有喷注面积可调的特征，还由于具有结构简单、工作可靠性高、成本低等优点，已经成为变推力液体火箭发动机中喷注器方案的优先选择。
针栓式喷注器运动件的调节通常采用机械调节(如电机驱动)或液压作动调节(如液压-弹簧平衡作动)。其中液压作动调节的自适应式可调针栓式喷注器，具有很好的适应性和稳定的喷雾燃烧效率，又具有结构紧凑简单的特点，是较为理想的变推力液体火箭发动机针栓式喷注器调节方案。
但目前液压作动调节的针栓式喷注器的中心调节组件装配的一致性较差，可操作性不高，会影响针栓式喷注器的工作可靠性。
为了规避上述技术问题带来的影响，第一方面，如图1与图2所示，本发明实施例提供一种针栓式喷注器，包括：壳体1、中心筒2、中心杆4以及针栓3。中心筒2位于壳体1内，且与壳体1固定连接，针栓3位于壳体1以及中心筒2之间，可沿壳体1的轴向运动。中心杆4位于中心筒2内，且与中心筒2固定连接。壳体1上开设有第一腔体11以及与第一腔体11相连通的第一推进剂流道，当第一推进剂沿第一腔体11进入第一推进剂流道时，在第一推进剂的作用下，针栓3沿壳体1的轴向运动，第一推进剂从第一推进剂流道进入针栓3与壳体1之间形成的第一间隙14中，并沿第一间隙14喷出。中心筒2上开设有第二腔体21以及与第二腔体21相连通的第二推进剂流道22，当第二推进剂沿第二腔体21进入第二推进剂流道22时，第二推进剂从中心杆4与中心筒2之间形成的第二间隙23喷出。其中，第一间隙14的中心线和第二间隙23的中心线具有交点。
具体实施时，在针栓式喷注器正常工作时，需要向第一腔体11内供入第一推进剂，当第一推进剂沿第一腔体11进入第一推进剂流道时，会在第一推进剂流道内充填容腔并建压，在第一推进剂产生的液压力作用下，针栓3沿壳体1的轴向向上运动，从而扩大第一间隙14的尺寸，以便第一推进剂沿第一间隙14喷出。同时，向第二腔体21内推入第二推进剂，第二推进剂沿第二推进剂流道22进入中心筒2与中心杆4形成的第二间隙23内，并从第二间隙23的出液口喷出。且当针栓3沿壳体1的轴向运动时，针栓3推向中心筒2的一端，向壳体1的上端运动，从而实现对第二间隙23的尺寸的调整。也就是，由于第二间隙23的出液口有部分被针栓3遮挡，在针栓3沿壳体1的轴向向上运动时，也会同步增大第二间隙23的出液口的尺寸，实现了对第二推进剂喷注面积的调节。在第一间隙14的中心线以及第二间隙23的中心线的交点处，第一推进剂以及第二推进剂撞击、混合和燃烧。
采用上述技术方案的情况下，中心筒2位于壳体1内，且与壳体1固定连接，针栓3位于壳体1以及中心筒2之间，可沿壳体1的轴向运动。中心杆4位于中心筒2内，且与中心筒2固定连接。如此，能够将中心杆4、中心筒2以及壳体1的相对位置固定，从而保证各零部件与壳体1同轴设置，且能够在针栓3沿壳体1的轴向运动时，避免针栓式喷注器的其他组件之间产生相对位移，影响组件调节的一致性。壳体1上开设有第一腔体11以及与第一腔体11相连通的第一推进剂流道，当第一推进剂沿第一腔体11进入第一推进剂流道时，在第一推进剂的作用下，针栓3沿壳体1的轴向运动，第一推进剂从第一推进剂流道进入针栓3与壳体1之间形成的第一间隙14中，并沿第一间隙14喷出。中心筒2上开设有第二腔体21以及与第二腔体21相连通的第二推进剂流道22，当第二推进剂沿第二腔体21进入第二推进剂流道22时，第二推进剂从中心杆4与中心筒2之间形成的第二间隙23喷出。且第一间隙14的中心线和第二间隙23的中心线具有交点。基于此，本发明实施例可以仅通过调整第一推进剂进入第一腔体11的流量，改变第一推进剂对针栓3的作用力，从而改变针栓3沿壳体1的轴向运动距离，以实现对于第一间隙14的尺寸的调整，当针栓3沿壳体1的轴向运动时，针栓3推向中心筒2的一端，向壳体1的上端运动，从而实现第二间隙23的尺寸的调整，使得第一推进剂与第二推进剂在交点处撞击、混合和燃烧的效率也会产生相应的改变，可操作性得到增强。由此可见，本发明实施例提供的针栓式喷注器不仅在组件装配方面具有一致性，还具有可操作性较强的优点，能够在一定程度上避免因为操作不当造成的不良影响，从而提高其工作的可靠性。
在实际应用中，中心筒2与壳体1之间通过压环7固定连接，精密配合定位中心筒2，将中心筒2牢靠固定在壳体1上。中心杆4与中心筒2之间通过自锁螺母8固定连接，精密配合定位中心杆4，最终实现壳体1、针栓3、中心筒2以及中心杆4同轴设置。且在中心杆4与中心筒2之间的连接处形成周向通道，使得第二腔体21内的第二推进剂可以沿着该周向通道进入第二推进剂流道22。可以理解的是，以上压环7以及自锁螺母8仅为举例，在选用其他螺纹紧固件时，也应保证中心筒2与壳体1的连接处，以及中心筒2与中心杆4的连接处完全贴合，本发明实施例对此不做限定。
需要说明的是，第一推进剂一般为燃料推进剂，第二推进剂一般为氧化剂推进剂，本发明实施例对此不做限定。
此外，为了适应高温工作环境，中心筒2与针栓3通常选择高温合金材料，即温度范围满足常温至800℃，且针栓3材料的线膨胀系数应高于中心筒2材料，以避免升温后针栓3与中心筒2之间的间隙变小，导致针栓3卡死，影响针栓式喷注器的正常工作。
在一种可能的实现方式中，如图1和图2所示，第一间隙14沿壳体1轴向设置，第二间隙23沿中心筒2径向设置。具体的，第一间隙14沿壳体1轴向设置，且沿壳体1的周向均匀布设，最终形成轴向喷注的外圈环形间隙。第二间隙23沿中心筒2径向设置，且沿中心筒2的周向均匀布设，最终形成径向喷注的内圈环形间隙。基于此，两个环形的中心线必然会有交点，使得第一推进剂与第二推进剂在两个环形间隙的交点处碰撞、混合和燃烧，从而产生推力室所需的推力。
在一种可能的实现方式中，如图1所示，第一推进剂流道包括第一子流道12以及第二子流道13。第一子流道12沿壳体1的轴向设置，第一子流道12的进液口与第一腔体11相连通，出液口与针栓3的第一端接触，在第一推进剂沿第一腔体11进入第一子流道12时，在第一推进剂的作用下，针栓3沿壳体1的轴向运动。
第二子流道13沿壳体1的径向设置，第二子流道13的进液口与第一腔体11连通，出液口与第一间隙14连通，在第一推进剂沿第一腔体11进入第二子流道13时，第一推进剂从第二子流道13进入第一间隙14中，并沿第一间隙14喷出。
可以理解的是，在第一推进剂沿第一腔体11进入第一子流道12时，第一子流道12内的第一推进剂会产生液压作动力，且第一子流道12的出液口与针栓3的第一端接触，液压作动力向针栓3的第一端提供沿壳体1的轴向向上的作用力，使得针栓3可以在液压作动力的作用下，向上运动。在第一推进剂进入第一腔体11后，会沿着第一腔体11出液口的方向分别注入第一子流道12以及第二子流道13，因此在针栓3向上运动的同时，第一推进剂也会沿着第二子流道13进入第一间隙14中，最终从第一间隙14的出液口喷出。基于此，在调整第一推进剂进入的流量时，第一子流道12的容积随着变化，会相应改变针栓3向上运动的距离，从而调整第一间隙14的尺寸，最终实现对第一推进剂喷出面积的调整。
在一种可能的实现方式中，当第一推进剂的作用力增大时，第一间隙14的尺寸以及第二间隙23的出液口的尺寸同时增加。请参阅图1和图2，针栓3的第一端与第一子流道12接触，针栓3的第二端还同时与第二间隙23的出液口接触，且针栓3的第二端是逐渐缩小的结构。基于此，在第一推进剂的作用力增大时，也就意味着对针栓3向上运动的作用力增大，使得针栓3沿壳体1的轴向向上运动，第一间隙14的尺寸会逐渐增加，同时针栓3的第二端也会远离第二间隙23的出液口，使得对于第二间隙23出液口的遮蔽部分会逐渐减少，即也会增加第二间隙23出液口的面积，从而使得第一推进剂以及第二推进剂的喷注面积同时增加，在撞击、混合和燃烧后产生更大的推力。
在一些实施例中，壳体1具有第一限位面15，第一限位面15位于第一子流道12的出液口的一侧，且第一限位面15靠近针栓3的第一端的第一侧。中心筒2具有第二限位面24，第二限位面24靠近针栓3的第一端的第二侧。第一限位面15与第二限位面24用于限定针栓3的轴向运动距离。
具体实施时，如图1所示，第一限位面15以及第二限位面24限制了针栓3运动的最低位置以及最高位置。可以理解的是，当针栓3的第一端位于最低位置时，即第一端与第一限位面15接触时，针栓3的第二端不会完全遮蔽第二间隙23的出液口，从而使得第二间隙23能够有第二推进剂喷出，同时，也需要令第一间隙14的尺寸满足针栓式喷注器初始工作时的喷注条件。当针栓3的第一端位于最高位置时，即第一端与第二限位面24接触时，针栓3不会完全脱离壳体1与中心筒2，仍被限制在壳体1与中心筒2之间，使得第一间隙14可以稳定喷出第一推进剂，喷注器仍可以稳定工作。在实际中，第一限位面15可以与壳体1可拆卸连接，也可以与壳体1一体成型。同样的，第二限位面24也可以与中心筒2一体成型，或与中心筒2可拆卸的连接。例如，第二限位面24可以为中心筒2上的限位台阶，即如图1所示的凸台结构，本发明实施例对此不做具体限定。
示例性的，如图1所示，针栓式喷注器还包括弹性组件5，弹性组件5位于针栓3的第一端与中心筒2之间。弹性组件5的第一端与针栓3的第一端的第二侧接触，弹性组件5的第二端与中心筒2的另一端接触。
当第一推进剂未进入第一子流道12时，在弹性组件5的作用下，针栓3的第一端的第一侧与第一限位面15接触。当第一推进剂进入第一子流道12时，在第一推进剂的作用下，针栓3向背离所述第一限位面15的一侧运动，针栓3的第一端的第一侧与第一限位面15之间具有第三间隙。
具体的，弹性组件5作用于针栓3的第一端，且弹性组件5的作用力与液压作动力是完全反向的力。当进入第一子流道12的第一推进剂流量发生变化时，即液压作动力发生变化时，弹性组件5也会相应的改变对针栓3的作用力，使得针栓3在两个作用力的平衡下能够重新实现调节和定位，从而实现推力调节时喷注的同步调节，保证针栓式喷注器的稳定工作。
在实际中，弹性组件5包括垫环52和弹簧51，且可以通过调整垫环52的厚度，使弹簧51产生一定的初始压缩量，一方面可以实现弹簧51在调节范围内刚度的线性变化，另一方面，也能够使弹簧51具有预紧力，从而防止针栓3在非工作期间运动，并使其具有承受飞行过载能力。
此外，由于中心筒2上具有第二限位面24，还能够防止弹簧51过压缩，或在发生弹簧51断裂导致针栓3调节失效的情况下，使得针栓3能够固定位置，保证针栓式喷注器稳定工作，进一步提高其工作可靠性。
在一种可能的实现方式中，如图1所示，针栓式喷注器还包括调整垫片6，调整垫片6位于中心筒2与壳体1之间，用于调整中心筒2与壳体1的相对位置。在实际中，使用调整垫片6调整中心筒2与壳体1的相对位置，使得中心筒2与壳体1中心同轴，且不会遮蔽第二间隙23的出液口，从而使得第二间隙23出液口的尺寸能够满足针栓式喷注器初始工作时的喷注条件。
在一种可能的实现方式中，如图1所示，针栓式喷注器还包括第一密封圈91以及第二密封圈92。第一密封圈91设置于针栓3与壳体1之间。第二密封圈92设置于针栓3内壁与中心筒2的外壁之间。基于此，第一密封圈91位于针栓3的第一端与壳体1之间，用于密封第一子流道12内的第一推进剂，以避免第一推进剂的泄露，从而造成调节失效。第二密封圈92位于针栓3的内壁与中心筒2的外壁之间，用于密封针栓式喷注器工作时产生的燃气，用于避免热量逸散，从而降低第一推进剂以及第二推进剂的燃烧效率，而且燃气逸散也会直接影响针栓式喷注器的性能，导致发动机的推力室产生的推力降低。
在一种可能的实现方式中，如图1所示，针栓3的内壁与中心筒2的外壁之间具有第一配合间隙以及第二配合间隙。第一配合间隙远离第一间隙14的出液口设置，第一配合间隙的尺寸为0.01mm至0.02mm。第二配合间隙靠近第一间隙14的出液口设置，第二配合间隙的尺寸为0.005mm至0.01mm。中心筒2与壳体1之间具有第三配合间隙，第三配合间隙为环形配合间隙，环形配合间隙的尺寸为0.005mm至0.01mm。具体的，如图1所示，第一配合间隙和第二配合间隙位于中心筒2的圆柱段的外壁与针栓3的内部之间，第三配合间隙靠近压环7设置。如此。就能够保证针栓3的灵活运动，防止针栓3的内壁与中心筒2的外壁产生多余的摩擦，以及中心筒2的外壁与壳体1之间准确同轴定位，且在调节第一推进剂的流量的过程中，也不会造成针栓3的卡滞，在升温后，也能避免针栓3卡死，影响针栓式喷注器的正常工作。
第二方面，本发明实施例提供一种推力室，包括燃烧室、喷管组件以及针栓式喷注器。针栓式喷注器用于将第一路推进剂以及第二路推进剂喷入燃烧室内，以使第一路推进剂以及第二路推进剂在燃烧室内撞击、混合和燃烧。燃烧室用于容纳第一路推进剂以及第二路推进剂撞击、混合和燃烧后的燃烧产物。喷管组件用于将燃烧产物喷出，以产生推力室所需的推力。
第二方面提供的推力室的有益效果与第一方面或第一方面任一可能的实现方式所描述的针栓式喷注器的有益效果相同，此处不做赘述。
在上述实施方式的描述中，具体特征、结构、材料或者特点可以在任何的一个或多个实施例或示例中以合适的方式结合。
以上所述，仅为本发明的具体实施方式，但本发明的保护范围并不局限于此，任何熟悉本技术领域的技术人员在本发明揭露的技术范围内，可轻易想到变化或替换，都应涵盖在本发明的保护范围之内。因此，本发明的保护范围应以所述权利要求的保护范围为准。

Claims (10)

  1. 一种针栓式喷注器，其特征在于，所述针栓式喷注器包括：壳体、中心筒、中心杆以及针栓；其中：
    所述中心筒位于所述壳体内，且与所述壳体固定连接，所述针栓位于所述壳体以及所述中心筒之间，可沿所述壳体的轴向运动；所述中心杆位于所述中心筒内，且与所述中心筒固定连接；
    所述壳体上开设有第一腔体以及与所述第一腔体相连通的第一推进剂流道，当第一推进剂沿所述第一腔体进入所述第一推进剂流道时，在所述第一推进剂的作用下，所述针栓沿所述壳体的轴向运动，所述第一推进剂从所述第一推进剂流道进入所述针栓与所述壳体之间形成的第一间隙中，并沿所述第一间隙喷出；
    所述中心筒上开设有第二腔体以及与所述第二腔体相连通的第二推进剂流道，当第二推进剂沿所述第二腔体进入所述第二推进剂流道时，所述第二推进剂从所述中心杆与所述中心筒之间形成的第二间隙喷出；
    其中，所述第一间隙的中心线和所述第二间隙的中心线具有交点。
  2. 根据权利要求1所述的针栓式喷注器，其特征在于，所述第一间隙沿所述壳体轴向设置，所述第二间隙沿所述中心筒径向设置。
  3. 根据权利要求1所述的针栓式喷注器，其特征在于，所述第一推进剂流道包括第一子流道以及第二子流道；其中：
    所述第一子流道沿所述壳体的轴向设置，所述第一子流道的进液口与所述第一腔体相连通，出液口与所述针栓的第一端接触，在所述第一推进剂沿所述第一腔体进入所述第一子流道时，在所述第一推进剂的作用下，所述针栓沿所述壳体的轴向运动；
    所述第二子流道沿所述壳体的径向设置，所述第二子流道的进液口与所述第一腔体连通，出液口与所述第一间隙连通，在所述第一推进剂沿所述第一腔体进入所述第二子流道时，所述第一推进剂从所述第二子流道进入所述第一间隙中，并沿所述第一间隙喷出。
  4. 根据权利要求3所述的针栓式喷注器，其特征在于，所述壳体具有第一限位面，所述第一限位面位于所述第一子流道的出液口的一侧，且所述第一 限位面靠近所述针栓的第一端的第一侧；
    所述中心筒具有与第二限位面，所述第二限位面靠近所述针栓的第一端的第二侧；
    所述第一限位面与所述第二限位面用于限定所述针栓的轴向运动距离。
  5. 根据权利要求4所述的针栓式喷注器，其特征在于，所述针栓式喷注器还包括弹性组件，所述弹性组件位于所述针栓的第一端与所述中心筒之间；其中：
    所述弹性组件的第一端与所述针栓的第一端的第二侧接触，所述弹性组件的第二端与所述中心筒的另一端接触；
    当所述第一推进剂未进入所述第一子流道时，在所述弹性组件的作用下，所述针栓的第一端的第一侧与所述第一限位面接触；
    当所述第一推进剂进入所述第一子流道时，在所述第一推进剂的作用下，所述针栓向背离所述第一限位面的一侧运动，所述针栓的第一端的第一侧与所述第一限位面之间具有第三间隙。
  6. 根据权利要求1至5任一项所述的针栓式喷注器，其特征在于，当所述第一推进剂的作用力增大时，所述第一间隙的出液口的尺寸以及所述第二间隙的出液口的尺寸同时增加。
  7. 根据权利要求1至5任一项所述的针栓式喷注器，其特征在于，所述针栓式喷注器还包括调整垫片，所述调整垫片位于所述中心筒与所述壳体之间，用于调整所述中心筒与所述壳体的相对位置。
  8. 根据权利要求1至5任一项所述的针栓式喷注器，其特征在于，所述针栓式喷注器还包括第一密封圈以及第二密封圈；
    所述第一密封圈设置于所述针栓与所述壳体之间；所述第二密封圈设置于所述针栓的内壁与所述中心筒的外壁之间。
  9. 根据权利要求1至5任一项所述的针栓式喷注器，其特征在于，所述针栓的内壁与所述中心筒的外壁之间具有第一配合间隙以及第二配合间隙；
    所述第一配合间隙远离所述第一间隙的出液口设置，所述第一配合间隙的尺寸为0.01mm至0.02mm；
    所述第二配合间隙靠近所述第一间隙的出液口设置，所述第二配合间隙的尺寸为0.005mm至0.01mm；
    所述中心筒与所述壳体之间具有第三配合间隙，所述第三配合间隙为环形配合间隙，所述环形配合间隙的尺寸为0.005mm至0.01mm。
  10. 一种推力室，其特征在于，所述推力室包括燃烧室、喷管组件以及如权利要求1至9任一项所述的针栓式喷注器；其中：
    所述针栓式喷注器用于将第一路推进剂以及第二路推进剂喷入所述燃烧室内，以使所述第一路推进剂以及所述第二路推进剂在所述燃烧室内撞击、混合和燃烧；
    所述燃烧室用于容纳所述第一路推进剂以及所述第二路推进剂撞击、混合和燃烧后的燃烧产物；
    所述喷管组件用于将所述燃烧产物喷出，以产生所述推力室所需的推力。
PCT/CN2023/079696 2022-03-21 2023-03-04 一种针栓式喷注器及推力室 WO2023179343A1 (zh)

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