CN116853530A - Storage tank embedded type propulsion stage - Google Patents

Storage tank embedded type propulsion stage Download PDF

Info

Publication number
CN116853530A
CN116853530A CN202310794483.6A CN202310794483A CN116853530A CN 116853530 A CN116853530 A CN 116853530A CN 202310794483 A CN202310794483 A CN 202310794483A CN 116853530 A CN116853530 A CN 116853530A
Authority
CN
China
Prior art keywords
tank
load
propulsion stage
storage tank
embedded
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202310794483.6A
Other languages
Chinese (zh)
Inventor
朱俊杰
柴煜
欧阳文
张蕊瑞
沈涛
柳征勇
靳宗向
肖余之
张玲
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Shanghai Aerospace System Engineering Institute
Original Assignee
Shanghai Aerospace System Engineering Institute
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Shanghai Aerospace System Engineering Institute filed Critical Shanghai Aerospace System Engineering Institute
Priority to CN202310794483.6A priority Critical patent/CN116853530A/en
Publication of CN116853530A publication Critical patent/CN116853530A/en
Pending legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64GCOSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00Cosmonautic vehicles
    • B64G1/22Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40Arrangements or adaptations of propulsion systems
    • B64G1/402Propellant tanks; Feeding propellants

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)

Abstract

The invention discloses a storage tank embedded propulsion stage, which comprises a bearing cylinder, a propellant storage tank, a high-pressure gas cylinder, a gas cylinder bracket, a main engine and a main engine mounting bracket, wherein the bearing cylinder is arranged on the main engine mounting bracket; the side wall of the bearing cylinder is uniformly provided with a circular storage tank mounting flange; the propellant storage tank is embedded into the bearing cylinder through an opening of the storage tank mounting flange and is connected with the bearing cylinder through the storage tank mounting flange; each high-pressure gas cylinder is respectively arranged at the interval of two adjacent storage tank mounting flanges through a gas cylinder bracket; the main engine is mounted to the rear end of the propulsion stage through a main engine mounting bracket and is coaxial with the bearing cylinder. The embedded propulsion stage of the storage tank realizes the installation of the high-capacity propellant storage tank under the constraint of smaller transverse envelope, and forms a propulsion module which has compact structure, lighter total weight and large speed increment. The invention can also realize the launching of one arrow with two stars and multiple stars.

Description

一种贮箱内嵌式推进级A tank-embedded propulsion stage

技术领域Technical field

本发明涉及一种推进级构型,主要应用于中高轨卫星的轨道转移。The invention relates to a propulsion stage configuration, which is mainly used for orbit transfer of medium and high orbit satellites.

背景技术Background technique

由于变轨或轨道机动的需求,中高轨卫星、深空探测飞行器等航天器一般装备有用于轨道控制的大推力主发动机,并需要携带大量推进剂,推进剂总重甚至超过了整个航天器的50%。而由此带来的贮箱、管路阀路等干重,在航天器入轨后将成为“费重”,在后续的变轨中将带来额外的推进剂浪费。因此,可采用独立的上面级或推进级,完成轨道入轨后将其分离抛弃,优化在轨执行任务的航天器的结构与重量。而对于这类上面级或推进级,巨量的推进剂携带需求,导致推进剂贮箱的尺寸和数量增加,势必造成航天器推进级尺寸的增大。而有限的运载火箭整流罩包络和发射重量的限制,与之形成了十分突出的矛盾。Due to the need for orbit change or orbital maneuvering, spacecraft such as medium and high orbit satellites and deep space exploration vehicles are generally equipped with high-thrust main engines for orbit control and need to carry a large amount of propellant. The total propellant weight even exceeds the weight of the entire spacecraft. 50%. The resulting dry weight of tanks, pipelines, valves, etc. will become "costly weight" after the spacecraft enters orbit, and will cause additional waste of propellant during subsequent orbit changes. Therefore, an independent upper stage or propulsion stage can be used, which can be separated and discarded after the orbit is completed to optimize the structure and weight of the spacecraft performing missions in orbit. For this type of upper stage or propulsion stage, the huge amount of propellant carrying requirements leads to an increase in the size and number of propellant tanks, which will inevitably lead to an increase in the size of the spacecraft propulsion stage. The limited launch vehicle fairing envelope and launch weight restrictions have formed a very prominent contradiction.

常规飞行器采用中心承力筒或外承力筒构型:前者一般将推进剂贮箱布置在中心承力筒内部,不仅质心被抬高,且布置贮箱数量有限(一般为2个),少数中心承力筒构型的卫星采用4个贮箱平铺在中心承力筒外部的箱板结构上,虽然满足了推进剂携带量的需求,但占据了仪器设备的布局空间,却同时浪费了中心承力筒内部的空间;外承力筒构型虽可以实现多个贮箱平铺为模块安装,但结构尺寸和重量均有所上升,难以兼顾大量推进剂需求情况下紧凑的构型布局包络和轻量化需求。Conventional aircraft adopt a central load-bearing cylinder or an external load-bearing cylinder configuration: the former generally arranges the propellant storage tank inside the central load-bearing cylinder, which not only raises the center of mass, but also has a limited number of arranged storage tanks (usually 2). Satellites with a central load-bearing tube configuration use four storage tanks laid flat on the box plate structure outside the central load-bearing tube. Although it meets the demand for propellant carrying capacity, it occupies the layout space of instruments and equipment and wastes time at the same time. The space inside the central load-bearing cylinder; although the outer load-bearing cylinder configuration can realize the installation of multiple tanks flat as modules, the structural size and weight have increased, making it difficult to take into account the compact configuration layout when a large amount of propellant is required. Envelopment and lightweight requirements.

发明内容Contents of the invention

本发明所要解决的技术问题是:本发明提供一种贮箱内嵌式推进级,在实现大容量推进剂贮箱的安装的同时,实现结构形式简单、布局紧凑、总重较轻。The technical problem to be solved by the present invention is: the present invention provides a tank-embedded propulsion stage, which can realize the installation of a large-capacity propellant tank while achieving a simple structure, a compact layout, and a light overall weight.

本发明所采用的技术方案是:一种贮箱内嵌式推进级,包括承力筒、推进剂贮箱、高压气瓶、气瓶支架、主发动机和主发动机安装支架;承力筒侧壁均布圆环形的贮箱安装法兰;推进剂贮箱通过贮箱安装法兰的开孔嵌入承力筒内部,并通过贮箱安装法兰与承力筒连接;各高压气瓶通过气瓶支架分别安装在相邻两个贮箱安装法兰间隔处;主发动机通过主发动机安装支架安装至推进级后端,与承力筒同轴。The technical solution adopted by the present invention is: a storage tank-embedded propulsion stage, including a load-bearing cylinder, a propellant storage tank, a high-pressure gas cylinder, a gas cylinder bracket, a main engine and a main engine mounting bracket; the side wall of the load-bearing cylinder A uniformly distributed annular tank installation flange; the propellant tank is embedded into the load-bearing cylinder through the opening of the tank installation flange, and is connected to the load-bearing cylinder through the tank installation flange; each high-pressure gas bottle passes through the gas The bottle brackets are installed at the intervals between the mounting flanges of two adjacent storage tanks; the main engine is installed to the rear end of the propulsion stage through the main engine mounting bracket, coaxially with the load-bearing cylinder.

进一步的,所述承力筒为圆柱形,上端面设置舱段对接框,用于对接航天器其它舱段;下端面设置星箭连接框,用于与运载火箭支撑舱连接。Furthermore, the load-bearing tube is cylindrical, with a cabin section docking frame set on the upper end face for docking with other cabin sections of the spacecraft; and a star-arrow connection frame set on the lower end face for connection with the launch vehicle support cabin.

进一步的,所述承力筒的壁板采用机铣或化铣壁板进行焊接或螺接连接成形;舱段对接框、星箭连接框和贮箱安装法兰采用锻件机加工成形。Furthermore, the wall plate of the load-bearing tube is formed by machine milling or chemical milling of the wall plate for welding or screw connection; the cabin docking frame, the star arrow connection frame and the storage tank mounting flange are formed by forging machining.

进一步的,所述推进级贮箱的直径小于贮箱安装法兰的开孔,通过铰制孔螺栓将推进级贮箱的法兰与贮箱安装法兰连接。Further, the diameter of the propulsion stage tank is smaller than the opening of the tank mounting flange, and the flange of the propulsion stage tank is connected to the tank mounting flange through reamed hole bolts.

进一步的,所述高压气瓶采用碳纤维复合材料缠绕铝合金内胆。Furthermore, the high-pressure gas cylinder uses carbon fiber composite material to wrap the aluminum alloy liner.

进一步的,所述气瓶支架包括底座和条带,底座对高压气瓶进行轴向约束并承载,条带对高压气瓶进行横向约束并承载。Further, the gas bottle bracket includes a base and a strip. The base axially restrains and carries the high-pressure gas bottle, and the strip lateral restrains and carries the high-pressure gas bottle.

进一步的,所述底座采用铝合金机加工制造。Furthermore, the base is machined and manufactured from aluminum alloy.

进一步的,所述条带采用不锈钢片裁制。Furthermore, the strips are cut from stainless steel sheets.

进一步的,所述主发动机安装支架包括法兰盘、撑杆和安装座;法兰盘用于连接主发动机,安装座连接至承力筒内壁,撑杆连接法兰盘与安装座,撑杆采用碳纤维复合材料。Further, the main engine mounting bracket includes a flange, a strut and a mounting base; the flange is used to connect the main engine, the mounting base is connected to the inner wall of the load-bearing tube, the strut connects the flange and the mounting base, and the strut Made of carbon fiber composite material.

进一步的,所述贮箱内嵌式推进级通过设置多星发射过渡段,实现一箭双星或多星发射。Furthermore, the tank-embedded propulsion stage realizes dual-star or multi-star launch with one rocket by setting a multi-star launch transition section.

与现有技术相比,本发明的有益效果如下:Compared with the prior art, the beneficial effects of the present invention are as follows:

(1)本发明的推进级采用大容积贮箱内嵌式承力筒构型,特别适用于运载火箭整流罩包络较小,且航天器推进剂携带量需求又较多的任务。可以实现大容量推进剂携带,提供轨道转移所需的大速度增量,具有结构紧凑、质量轻、承载能力高的特点。(1) The propulsion stage of the present invention adopts the configuration of a large-volume storage tank with an embedded load-bearing tube, which is particularly suitable for missions where the launch vehicle fairing envelope is small and the spacecraft propellant carrying capacity is large. It can carry large-capacity propellant and provide large speed increments required for orbital transfer. It has the characteristics of compact structure, light weight and high carrying capacity.

(2)本发明的贮箱内嵌式推进级,在实现大容量推进剂贮箱的安装的同时,实现了结构形式简单、布局紧凑、总重较轻。本发明的贮箱内嵌式推进级可以应用于卫星、货运飞船、深空探测飞行器等航天器,可以在满足较小的运载火箭整流罩包络约束的情况下,提供大速度增量。同时本发明可以通过增加过渡段实现多星串联、并联的发射。(2) The tank-embedded propulsion stage of the present invention not only realizes the installation of a large-capacity propellant tank, but also achieves a simple structural form, a compact layout, and a light overall weight. The tank-embedded propulsion stage of the present invention can be applied to spacecraft such as satellites, cargo spacecraft, and deep space exploration aircraft, and can provide large speed increments while meeting the envelope constraints of smaller launch vehicle fairings. At the same time, the present invention can realize series and parallel launch of multiple satellites by adding transition sections.

附图说明Description of the drawings

图1是本发明实施例的总体构型与组成示意图;Figure 1 is a schematic diagram of the overall configuration and composition of an embodiment of the present invention;

图2是本发明实施例的承力筒的结构组成示意图;Figure 2 is a schematic diagram of the structural composition of the load-bearing tube according to the embodiment of the present invention;

图3是本发明实施例的推进剂贮箱的安装示意图;Figure 3 is a schematic diagram of the installation of the propellant tank according to the embodiment of the present invention;

图4是本发明实施例的高压气瓶与气瓶支架及主发动机与主发动机安装支架的安装示意图;Figure 4 is an installation schematic diagram of the high-pressure gas bottle and the gas bottle bracket and the main engine and the main engine mounting bracket according to the embodiment of the present invention;

图5是本发明实施例的多星串联承载发射示意图;Figure 5 is a schematic diagram of multi-satellite series load-carrying launch according to the embodiment of the present invention;

图6是本发明实施例的过渡段以及多星并联承载发射示意图。Fig. 6 is a schematic diagram of the transition section and multi-satellite parallel transmission according to the embodiment of the present invention.

具体实施方式Detailed ways

以下将结合附图对本发明提供的一种贮箱内嵌式推进级进行详细的描述,本实施例在以本发明技术方案为前提下进行实施,给出了详细的实施方式和具体的操作过程,但本发明的保护范围不限于下述的实施例,本领域技术人员在不改变本发明精神和内容的范围内,能够对其进行修改和润色。A tank-embedded propulsion stage provided by the present invention will be described in detail below with reference to the accompanying drawings. This embodiment is implemented on the premise of the technical solution of the present invention, and detailed implementation modes and specific operating procedures are given. , but the protection scope of the present invention is not limited to the following embodiments. Those skilled in the art can modify and polish them without changing the spirit and content of the present invention.

图1是本发明实施例的系统组成爆炸图。一种贮箱内嵌式推进级8,包括承力筒1、推进剂贮箱2、高压气瓶3、气瓶支架4、主发动机5及主发动机安装支架6。其中,承力筒1是整个舱体的支撑结构,采用圆柱形承力筒构型,具备良好的整体刚度和承载能力。承力筒1侧壁均布设置4个大开孔的圆环形贮箱安装法兰11,推进剂贮箱2通过该法兰开孔嵌入承力筒1内部,并通过贮箱安装法兰11实现连接。高压气瓶3通过气瓶支架4安装至承力筒1的4个贮箱安装法兰11间隔处。主发动机5通过主发动机安装支架6安装至推进级后端,与航天器舱体同轴。Figure 1 is an exploded view of system components according to an embodiment of the present invention. A tank-embedded propulsion stage 8 includes a load-bearing cylinder 1, a propellant tank 2, a high-pressure gas cylinder 3, a gas cylinder bracket 4, a main engine 5 and a main engine mounting bracket 6. Among them, the load-bearing tube 1 is the support structure of the entire cabin. It adopts a cylindrical load-bearing tube configuration and has good overall stiffness and load-bearing capacity. Four annular tank mounting flanges 11 with large openings are evenly arranged on the side wall of the load-bearing cylinder 1. The propellant tank 2 is embedded into the inside of the load-bearing cylinder 1 through the flange openings, and is installed through the tank installation flange. 11Achieve connection. The high-pressure gas cylinder 3 is installed at the intervals of the four storage tank mounting flanges 11 of the load-bearing cylinder 1 through the gas cylinder bracket 4. The main engine 5 is installed to the rear end of the propulsion stage through the main engine mounting bracket 6 and is coaxial with the spacecraft cabin.

参见图2,承力筒1包括:上端面为舱段对接框12,用于与航天器的其它舱段对接安装;下端面为星箭连接框13,用于与运载火箭支撑舱连接,可根据任务需求选用包带或点式连接方式;周向为4个均布的贮箱安装法兰11,以及承力筒壁板14。其中,贮箱安装法兰11开设大直径圆孔,其直径大于推进剂贮箱2的直径,以使推进剂贮箱2嵌入承力筒1内部。整个承力筒1的壁板14可采用机铣或化铣壁板进行焊接或螺接工艺连接成形。舱段对接框、星箭连接框和贮箱安装法兰可以采用锻件机加工成形。Referring to Figure 2, the load-bearing tube 1 includes: the upper end face is a cabin docking frame 12, which is used for docking and installation with other cabin sections of the spacecraft; the lower end face is a star-arrow connection frame 13, which is used to connect with the launch vehicle support cabin. The strap or point connection method is selected according to the task requirements; there are four evenly distributed storage tank installation flanges 11 in the circumference, and the load-bearing tube wall plate 14. Among them, the tank mounting flange 11 is provided with a large-diameter circular hole whose diameter is larger than the diameter of the propellant tank 2 so that the propellant tank 2 can be embedded inside the load-bearing cylinder 1 . The wall panels 14 of the entire load-bearing tube 1 can be connected and formed by machine milling or chemical milling of the wall panels through welding or screwing processes. The cabin docking frame, star-arrow connection frame and tank mounting flange can be machined using forgings.

推进剂贮箱2的几何中心应位于承力筒1壁板厚度的中心面。The geometric center of the propellant tank 2 should be located on the center plane of the wall plate thickness of the load-bearing cylinder 1.

参见图3,推进剂贮箱2的法兰21通过连接螺栓22与承力筒1的贮箱安装法兰11连接。Referring to Figure 3, the flange 21 of the propellant tank 2 is connected to the tank mounting flange 11 of the load-bearing cylinder 1 through connecting bolts 22.

此连接螺栓22选用铰制孔螺栓,相比普通螺栓可以承受更大的贮箱在发射过程中产生的沿飞行方向的剪切载荷。当然,也可根据实际需要,采用抗剪切锥套、减载销等结构实现剪切力的承载。This connecting bolt 22 adopts a reamed hole bolt, which can withstand a larger shear load along the flight direction generated by the tank during the launch process than ordinary bolts. Of course, according to actual needs, shear-resistant taper sleeves, load-reducing pins and other structures can be used to carry the shear force.

参见图4,高压气瓶3通过气瓶支架4安装至承力筒1的4个贮箱安装法兰11间隔处,正好利用了承力筒1的外侧剩余空间。Referring to Figure 4, the high-pressure gas cylinder 3 is installed at the intervals between the four storage tank mounting flanges 11 of the load-bearing cylinder 1 through the gas cylinder bracket 4, making full use of the remaining space outside the load-bearing cylinder 1.

高压气瓶3采用碳纤维复合材料缠绕铝合金内胆的设计,以实现高承压和轻量化。The high-pressure gas cylinder 3 is designed with an aluminum alloy liner wrapped with carbon fiber composite material to achieve high pressure bearing and lightweight.

参见图4,气瓶支架4由底座41和条带42组成,底座41实现对高压气瓶3轴向约束并承载,条带42实现对高压气瓶3横向约束并承载,并通过螺钉螺母实现紧箍力的调节。Referring to Figure 4, the gas cylinder bracket 4 is composed of a base 41 and a strip 42. The base 41 axially restrains and carries the high-pressure gas cylinder 3, and the strip 42 laterally restrains and carries the high-pressure gas bottle 3 through screws and nuts. Adjustment of tightening force.

气瓶支架4底座41采用铝合金机加工制造,气瓶支架4条带42采用不锈钢片裁制,并通过螺钉螺母实现紧箍力的调节,以此保证合适的连接强度、刚度。The base 41 of the gas bottle bracket 4 is machined from aluminum alloy, and the straps 42 of the gas bottle bracket 4 are cut from stainless steel sheets, and the tightening force is adjusted through screws and nuts to ensure appropriate connection strength and stiffness.

参见图4,主发动机5通过主发动机安装支架6安装至推进级后端,与舱体同轴。主发动机安装支架6由法兰盘61、撑杆62和安装座63组成。其中,法兰盘62用于连接主发动机5,安装座63用于连接至承力筒1内壁;撑杆62连接法兰盘62与安装座63,实现结构连接和承载,。Referring to Figure 4, the main engine 5 is installed to the rear end of the propulsion stage through the main engine mounting bracket 6, coaxially with the cabin. The main engine mounting bracket 6 is composed of a flange 61, a support rod 62 and a mounting base 63. Among them, the flange 62 is used to connect the main engine 5, and the mounting base 63 is used to connect to the inner wall of the load-bearing cylinder 1; the support rod 62 connects the flange 62 and the mounting base 63 to achieve structural connection and load-bearing.

主发动机安装支架6的法兰盘61和安装座63可采用金属材料,通过机加工制造。The flange 61 and the mounting seat 63 of the main engine mounting bracket 6 can be made of metal materials and manufactured by machining.

主发动机安装支架6的撑杆62可采用碳纤维复合材料制造,保证强度、刚度的同时,实现轻量化。The strut 62 of the main engine mounting bracket 6 can be made of carbon fiber composite material to ensure strength and stiffness while achieving lightweight.

图5是本发明实施例的多星串联承载发射示意图,推进级8通过过渡段7连接承载星9,若干承载星9通过星间连接装置10串联;图6是本发明实施例的过渡段7以及多星并联承载发射示意图,若干承载星9并联,通过过渡段7连接推进级8。本发明可以通过设置多星发射过渡段7,实现一箭双星、多星发射。Figure 5 is a schematic diagram of multi-satellite series load-bearing launch according to the embodiment of the present invention. The propulsion stage 8 is connected to the load-bearing satellite 9 through the transition section 7, and several load-bearing satellites 9 are connected in series through the inter-satellite connection device 10; Figure 6 is the transition section 7 of the embodiment of the present invention. As well as a schematic diagram of multi-satellite parallel load-bearing launch, several load-bearing satellites 9 are connected in parallel and connected to the propulsion stage 8 through the transition section 7. The present invention can realize double-star or multi-star launch with one arrow by setting the multi-satellite launch transition section 7 .

以上公开的本发明优选实施例只是用于帮助阐述本发明。优选实施例并没有详尽叙述所有的细节,也不限制该发明仅为所述的具体实施方式。显然,根据本说明书的内容,可作很多的修改和变化。本说明书选取并具体描述这些实施例,是为了更好地解释本发明的原理和实际应用,从而使所属技术领域技术人员能很好地理解和利用本发明。本发明仅受权利要求书及其全部范围和等效物的限制。The preferred embodiments of the invention disclosed above are only intended to help illustrate the invention. The preferred embodiments do not describe all details, nor do they limit the invention to the specific implementations described. Obviously, many modifications and variations are possible in light of the contents of this specification. These embodiments are selected and described in detail in this specification to better explain the principles and practical applications of the present invention, so that those skilled in the art can better understand and utilize the present invention. The invention is limited only by the claims and their full scope and equivalents.

本发明未详细说明部分属于本领域技术人员公知技术。The parts of the present invention that are not described in detail are well known to those skilled in the art.

Claims (10)

1.一种贮箱内嵌式推进级,其特征在于,包括承力筒(1)、推进剂贮箱(2)、高压气瓶(3)、气瓶支架(4)、主发动机(5)和主发动机安装支架(6);承力筒(1)侧壁均布圆环形的贮箱安装法兰(11);推进剂贮箱(2)通过贮箱安装法兰(11)的开孔嵌入承力筒(1)内部,并通过贮箱安装法兰(11)与承力筒(1)连接;各高压气瓶(3)通过气瓶支架(4)分别安装在相邻两个贮箱安装法兰(11)间隔处;主发动机(5)通过主发动机安装支架(6)安装至推进级后端,与承力筒(1)同轴。1. A tank-embedded propulsion stage, characterized by including a load-bearing cylinder (1), a propellant tank (2), a high-pressure gas bottle (3), a gas bottle bracket (4), and a main engine (5 ) and the main engine mounting bracket (6); the side wall of the load-bearing cylinder (1) is evenly distributed with an annular tank mounting flange (11); the propellant tank (2) is connected through the tank mounting flange (11) The opening is embedded inside the load-bearing cylinder (1), and is connected to the load-bearing cylinder (1) through the storage tank installation flange (11); each high-pressure gas cylinder (3) is installed on two adjacent sides through the gas cylinder bracket (4). at intervals between two storage tank mounting flanges (11); the main engine (5) is installed to the rear end of the propulsion stage through the main engine mounting bracket (6) and is coaxial with the load-bearing cylinder (1). 2.根据权利要求1所述的贮箱内嵌式推进级,其特征在于,所述承力筒(1)为圆柱形,上端面设置舱段对接框(12),用于对接航天器其它舱段;下端面设置星箭连接框(13),用于与运载火箭支撑舱连接。2. The tank-embedded propulsion stage according to claim 1, characterized in that the load-bearing tube (1) is cylindrical, and a cabin docking frame (12) is provided on the upper end surface for docking with other parts of the spacecraft. Cabin section; a star-arrow connection frame (13) is provided on the lower end surface for connection with the launch vehicle support cabin. 3.根据权利要求2所述的贮箱内嵌式推进级,其特征在于,所述承力筒(1)的壁板(14)采用机铣或化铣壁板进行焊接或螺接连接成形;舱段对接框、星箭连接框和贮箱安装法兰采用锻件机加工成形。3. The storage tank built-in propulsion stage according to claim 2, characterized in that the wall plate (14) of the load-bearing cylinder (1) is formed by machine milling or chemical milling of the wall plate for welding or screw connection. ; The cabin docking frame, star-arrow connection frame and tank mounting flange are machined from forgings. 4.根据权利要求1所述的贮箱内嵌式推进级,其特征在于,所述推进级贮箱(2)的直径小于贮箱安装法兰(11)的开孔,通过铰制孔螺栓将推进级贮箱(2)的法兰(21)与贮箱安装法兰(11)连接。4. The tank-embedded propulsion stage according to claim 1, characterized in that the diameter of the propulsion stage tank (2) is smaller than the opening of the tank mounting flange (11), and the reamed hole bolts Connect the flange (21) of the propulsion stage tank (2) to the tank mounting flange (11). 5.根据权利要求1所述的贮箱内嵌式推进级,其特征在于,所述高压气瓶(3)采用碳纤维复合材料缠绕铝合金内胆。5. The tank-embedded propulsion stage according to claim 1, characterized in that the high-pressure gas cylinder (3) uses carbon fiber composite material to wrap an aluminum alloy liner. 6.根据权利要求1所述的贮箱内嵌式推进级,其特征在于,所述气瓶支架(4)包括底座(41)和条带(42),底座(41)对高压气瓶(3)进行轴向约束并承载,条带(42)对高压气瓶进行横向约束并承载。6. The storage tank-embedded propulsion stage according to claim 1, characterized in that the gas bottle bracket (4) includes a base (41) and a strip (42), and the base (41) supports the high-pressure gas bottle (41). 3) Perform axial restraint and load-bearing, and the strip (42) performs lateral restraint and load-bearing on the high-pressure gas cylinder. 7.根据权利要求6所述的贮箱内嵌式推进级,其特征在于,所述底座(41)采用铝合金机加工制造。7. The tank-embedded propulsion stage according to claim 6, characterized in that the base (41) is machined and manufactured from aluminum alloy. 8.根据权利要求6所述的贮箱内嵌式推进级,其特征在于,所述条带(42)采用不锈钢片裁制。8. The storage tank built-in propulsion stage according to claim 6, characterized in that the strip (42) is made of stainless steel sheets. 9.根据权利要求1所述的贮箱内嵌式推进级,其特征在于,所述主发动机安装支架(6)包括法兰盘(61)、撑杆(62)和安装座(63);法兰盘(62)用于连接主发动机(5),安装座(63)连接至承力筒(1)内壁,撑杆(62)连接法兰盘(62)与安装座(63),撑杆(62)采用碳纤维复合材料。9. The tank-embedded propulsion stage according to claim 1, characterized in that the main engine mounting bracket (6) includes a flange (61), a strut (62) and a mounting seat (63); The flange (62) is used to connect the main engine (5), the mounting base (63) is connected to the inner wall of the load-bearing cylinder (1), and the support rod (62) connects the flange (62) and the mounting base (63). The rod (62) is made of carbon fiber composite material. 10.根据权利要求1所述的贮箱内嵌式推进级,其特征在于,所述贮箱内嵌式推进级通过设置多星发射过渡段(7),实现一箭双星或多星发射。10. The tank-embedded propulsion stage according to claim 1, characterized in that the tank-embedded propulsion stage realizes dual-star or multi-star launch with one rocket by setting a multi-satellite launch transition section (7).
CN202310794483.6A 2023-06-30 2023-06-30 Storage tank embedded type propulsion stage Pending CN116853530A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202310794483.6A CN116853530A (en) 2023-06-30 2023-06-30 Storage tank embedded type propulsion stage

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310794483.6A CN116853530A (en) 2023-06-30 2023-06-30 Storage tank embedded type propulsion stage

Publications (1)

Publication Number Publication Date
CN116853530A true CN116853530A (en) 2023-10-10

Family

ID=88235140

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202310794483.6A Pending CN116853530A (en) 2023-06-30 2023-06-30 Storage tank embedded type propulsion stage

Country Status (1)

Country Link
CN (1) CN116853530A (en)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106628266A (en) * 2017-01-13 2017-05-10 哈尔滨工业大学 Suspended Composite Tank Structure
CN107161359A (en) * 2017-05-19 2017-09-15 上海宇航系统工程研究所 A kind of main structure and the aircraft propulsion die configuration for promoting tank Integration Design
CN109162831A (en) * 2018-09-05 2019-01-08 北京航空航天大学 Solid-liquid power engine and the rocket for applying it
CN211844957U (en) * 2020-09-26 2020-11-03 中国长征火箭有限公司 Split support and aircraft
CN113446130A (en) * 2021-06-11 2021-09-28 上海宇航系统工程研究所 Final-stage passivation method for liquid oxygen kerosene of carrier rocket
CN114229040A (en) * 2021-12-17 2022-03-25 中国长城工业集团有限公司 Separable independent propulsion cabin system

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106628266A (en) * 2017-01-13 2017-05-10 哈尔滨工业大学 Suspended Composite Tank Structure
CN107161359A (en) * 2017-05-19 2017-09-15 上海宇航系统工程研究所 A kind of main structure and the aircraft propulsion die configuration for promoting tank Integration Design
CN109162831A (en) * 2018-09-05 2019-01-08 北京航空航天大学 Solid-liquid power engine and the rocket for applying it
CN211844957U (en) * 2020-09-26 2020-11-03 中国长征火箭有限公司 Split support and aircraft
CN113446130A (en) * 2021-06-11 2021-09-28 上海宇航系统工程研究所 Final-stage passivation method for liquid oxygen kerosene of carrier rocket
CN114229040A (en) * 2021-12-17 2022-03-25 中国长城工业集团有限公司 Separable independent propulsion cabin system

Similar Documents

Publication Publication Date Title
US4451017A (en) Three stage rocket vehicle with parallel staging
CN110104222A (en) A kind of modularization propulsion service system promoted based on mixed mode
CN110104214A (en) A kind of in-orbit separable satellite booster service system
US20240246491A1 (en) Spacecraft with increased cargo capacities, and associated systems and methods
CN114264199B (en) General core-level-based combined body recovery rocket overall configuration
Levack et al. Evolution of low enriched uranium nuclear thermal propulsion vehicle and engine design
Komar Hercules single-stage reusable vehicle supporting a safe, affordable, and sustainable human lunar & mars campaign
WO2024087465A1 (en) Satellite-rocket-carrier integrated spacecraft
Daniluk et al. The past, present, and future of super-heavy launch vehicles for research and exploration of the Moon and Mars
CN116853530A (en) Storage tank embedded type propulsion stage
CN217125165U (en) A satellite power cabin structure capable of carrying large-capacity propellant
Mercer et al. Solar electric propulsion concepts for human space exploration
Kutter Distributed launch-enabling beyond LEO missions
CN116592716A (en) Solid-liquid mixed carrier rocket for carrying radiation with detection satellite
Asyushkin et al. Outcome of development and initial operational phases of Versatile Space Tugs of the Fregat type.
Rudman et al. The Centaur upper stage vehicle
RU2830531C1 (en) Small space tug
RU2808312C1 (en) Small booster
Smith Evolved composite structures for Atlas V
Whitehead Single stage to orbit mass budgets derived from propellant density and specific impulse
RU2775518C1 (en) Propulsion unit for liquid-propellant rockets with hydrogen and methane filling invariant fuel tanks with batch layout
Bianchi et al. Vega Launch Vehicle Propulsion Systems-An Overview of the 2004 Development Status
Austad The common centaur upper stage
Ziglar et al. Metallic Vs Inflatable Primary Structure: A Comprehensive Trade for a Mars Transit Habitat
HANSEN et al. Assessment of external tank for heavy lift launch vehicle tankage

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination