CN116853530A - Storage tank embedded type propulsion stage - Google Patents

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

A tank-embedded propulsion stage

Technical field

The invention relates to a propulsion stage configuration, which is mainly used for orbit transfer of medium and high orbit satellites.

Background technique

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.

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.

Contents of the invention

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.

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.

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.

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.

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.

Furthermore, the high-pressure gas cylinder uses carbon fiber composite material to wrap the aluminum alloy liner.

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.

Furthermore, the base is machined and manufactured from aluminum alloy.

Furthermore, the strips are cut from stainless steel sheets.

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.

Furthermore, the tank-embedded propulsion stage realizes dual-star or multi-star launch with one rocket by setting a multi-star launch transition section.

Compared with the prior art, the beneficial effects of the present invention are as follows:

(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) 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.

Description of the drawings

Figure 1 is a schematic diagram of the overall configuration and composition of an embodiment of the present invention;

Figure 2 is a schematic diagram of the structural composition of the load-bearing tube according to the embodiment of the present invention;

Figure 3 is a schematic diagram of the installation of the propellant tank according to the embodiment of the present invention;

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;

Figure 5 is a schematic diagram of multi-satellite series load-carrying launch according to the embodiment of the present invention;

Fig. 6 is a schematic diagram of the transition section and multi-satellite parallel transmission according to the embodiment of the present invention.

Detailed ways

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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 .

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.

The parts of the present invention that are not described in detail are well known to those skilled in the art.

Claims (10)

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. 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. 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. 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. 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. 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. The tank-embedded propulsion stage according to claim 6, characterized in that the base (41) is machined and manufactured from aluminum alloy. 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. 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. 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).