A tank-in-tank propulsion stage

Abstract

The application discloses a kind of storage tank embedded propelling stage, including force cylinder, propellant storage tank, high-pressure gas cylinder, gas cylinder support, main engine and main engine mounting support;Force cylinder side wall is evenly distributed annular storage tank mounting flange;Propellant storage tank is embedded inside force cylinder by the opening of storage tank mounting flange, and is connected with force cylinder by storage tank mounting flange;Each high-pressure gas cylinder is installed at the interval between adjacent two storage tank mounting flanges by gas cylinder support;Main engine is installed to the rear end of propelling stage by main engine mounting support, and is coaxial with force cylinder.The storage tank embedded propelling stage of the application realizes the installation of large-capacity propellant storage tank under the constraint of smaller lateral envelope, forms a compact structure, total weight is lighter, and has the propelling module for providing large speed increment.The application can also realize one rocket double star, multiple star launch.

Description

Technical Field

[0001] This invention relates to a propulsion stage configuration, primarily used for orbit transfer of medium- and high-orbit satellites. Background Technology

[0002] Due to the need for orbital maneuvers or maneuvers, spacecraft such as medium- and high-orbit satellites and deep-space exploration vehicles are generally equipped with high-thrust main engines for orbital control and need to carry a large amount of propellant, with the total weight of propellant sometimes exceeding 50% of the entire spacecraft. The resulting dry weight of tanks, piping, and valves becomes "waste weight" after the spacecraft enters orbit, leading to additional propellant waste during subsequent orbital maneuvers. Therefore, a separate upper stage or propulsion stage can be used, separating and jettisoning it after orbital insertion, optimizing the structure and weight of the spacecraft performing its mission in orbit. However, the massive propellant carrying requirements for such upper stages or propulsion stages lead to an increase in the size and number of propellant tanks, inevitably resulting in an increase in the size of the spacecraft's propulsion stage. This presents a significant contradiction with the limitations of the launch vehicle's fairing envelope and launch weight.

[0003] Conventional spacecraft employ either a central support tube or an external support tube configuration. The former typically places the propellant tanks inside the central support tube, which not only raises the center of gravity but also limits the number of tanks (usually two). A few satellites with a central support tube configuration use four tanks laid flat on a box-like structure outside the central support tube. While this meets the propellant carrying capacity requirements, it occupies space for instrumentation and equipment layout, and also wastes space inside the central support tube. The external support tube configuration allows multiple tanks to be laid flat as modules, but the structural size and weight increase, making it difficult to balance the compact configuration layout and lightweight requirements under conditions of large propellant demand. Summary of the Invention

[0004] The technical problem to be solved by the present invention is: the present invention provides a tank-embedded propulsion stage, which achieves the installation of a large-capacity propellant tank while realizing a simple structure, compact layout and light weight.

[0005] The technical solution adopted in this invention is: a tank-embedded propulsion stage, including a support cylinder, a propellant tank, a high-pressure gas cylinder, a gas cylinder bracket, a main engine, and a main engine mounting bracket; the support cylinder has annular tank mounting flanges evenly distributed on its sidewall; the propellant tank is embedded inside the support cylinder through the opening of the tank mounting flange and connected to the support cylinder through the tank mounting flange; each high-pressure gas cylinder is installed at the interval between two adjacent tank mounting flanges through the gas cylinder bracket; the main engine is installed to the rear end of the propulsion stage through the main engine mounting bracket and is coaxial with the support cylinder.

[0006] Furthermore, the load-bearing cylinder is cylindrical, with a module docking frame on the upper end for docking with other modules of the spacecraft; and a star-rocket connection frame on the lower end for connecting with the launch vehicle support module.

[0007] Furthermore, the wall panels of the load-bearing cylinder are formed by welding or bolting using machine-milled or chemically milled wall panels; the compartment docking frame, the star-rocket connection frame, and the tank mounting flange are formed by forging.

[0008] Furthermore, 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 by reamed bolts.

[0009] Furthermore, the high-pressure gas cylinder uses a carbon fiber composite material wrapped around an aluminum alloy inner liner.

[0010] Furthermore, the gas cylinder support includes a base and a strip. The base provides axial constraint and supports the high-pressure gas cylinder, while the strip provides lateral constraint and supports the high-pressure gas cylinder.

[0011] Furthermore, the base is manufactured using aluminum alloy machining.

[0012] Furthermore, the strip is made of stainless steel sheet.

[0013] Furthermore, 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 cylinder, and the strut connects the flange and the mounting base. The strut is made of carbon fiber composite material.

[0014] Furthermore, the tank-embedded propulsion stage can achieve the launch of two or more satellites with a single rocket by setting a multi-satellite launch transition section.

[0015] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0016] (1) The propulsion stage of this invention adopts a large-volume storage tank embedded in a load-bearing cylinder configuration, which is particularly suitable for missions where the fairing envelope of the launch vehicle is small and the spacecraft requires a large amount of propellant. It can achieve large-capacity propellant carrying, provide the large velocity increment required for orbital transfer, and has the characteristics of compact structure, light weight, and high load-bearing capacity.

[0017] (2) The tank-embedded propulsion stage of the present invention achieves a simple structure, compact layout, and light overall weight while enabling the installation of a large-capacity propellant tank. The tank-embedded propulsion stage of the present invention can be applied to spacecraft such as satellites, cargo spacecraft, and deep space exploration vehicles, providing a large velocity increment while meeting the constraints of a relatively small launch vehicle fairing envelope. Furthermore, the present invention can achieve multi-satellite tandem and parallel launches by adding a transition section. Attached Figure Description

[0018] Figure 1 This is a schematic diagram showing the overall configuration and composition of an embodiment of the present invention;

[0019] Figure 2 This is a schematic diagram of the structural composition of the load-bearing cylinder according to an embodiment of the present invention;

[0020] Figure 3 This is a schematic diagram of the installation of the propellant tank according to an embodiment of the present invention;

[0021] Figure 4 This is an installation diagram of the high-pressure gas cylinder and gas cylinder bracket and the main engine and main engine mounting bracket according to an embodiment of the present invention.

[0022] Figure 5 This is a schematic diagram of multi-satellite tandem launch according to an embodiment of the present invention;

[0023] Figure 6 This is a schematic diagram of the transition section and multi-satellite parallel launch in an embodiment of the present invention. Detailed Implementation

[0024] The following is a detailed description of a tank-embedded propulsion stage provided by the present invention, with reference to the accompanying drawings. This embodiment is implemented based on the technical solution of the present invention, and provides detailed implementation methods and specific operation processes. However, the scope of protection of the present invention is not limited to the following embodiments. Those skilled in the art can modify and refine it without changing the spirit and content of the present invention.

[0025] Figure 1 This is an exploded view of the system composition according to an embodiment of the present invention. A propulsion stage 8 with an embedded propellant tank includes a support cylinder 1, a propellant tank 2, a high-pressure gas cylinder 3, a gas cylinder support 4, a main engine 5, and a main engine mounting bracket 6. The support cylinder 1 is the supporting structure of the entire cabin, adopting a cylindrical support cylinder configuration, possessing good overall rigidity and load-bearing capacity. Four large-aperture annular propellant tank mounting flanges 11 are evenly distributed on the side wall of the support cylinder 1. The propellant tank 2 is embedded into the support cylinder 1 through these flange openings and connected via the propellant tank mounting flanges 11. The high-pressure gas cylinder 3 is mounted to the four propellant tank mounting flanges 11 of the support cylinder 1 via the gas cylinder support 4. The main engine 5 is mounted to the rear end of the propulsion stage via the main engine mounting bracket 6, coaxial with the spacecraft cabin.

[0026] See Figure 2The load-bearing cylinder 1 includes: an upper end face of a module docking frame 12 for docking and installation with other modules of the spacecraft; a lower end face of a satellite-rocket connection frame 13 for connection with the launch vehicle support module, which can be connected by straps or point connections depending on mission requirements; four evenly distributed tank mounting flanges 11 circumferentially; and load-bearing cylinder wall panels 14. The tank mounting flanges 11 have large-diameter circular holes, the diameter of which 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 entire load-bearing cylinder 1 wall panel 14 can be formed by machine milling or chemical milling and then welding or bolting. The module docking frame, the satellite-rocket connection frame, and the tank mounting flanges can be formed by forging.

[0027] The geometric center of the propellant tank 2 should be located at the center plane of the wall thickness of the load-bearing cylinder 1.

[0028] See Figure 3 The flange 21 of the propellant tank 2 is connected to the tank mounting flange 11 of the load-bearing cylinder 1 by connecting bolts 22.

[0029] This connecting bolt 22 is a reamed hole bolt, which can withstand greater shear loads along the flight direction generated by the propellant tank during launch compared to ordinary bolts. Of course, shear force bearing can also be achieved by using shear-resistant cone sleeves, load-reducing pins, or other structures, depending on actual needs.

[0030] See Figure 4 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, which makes good use of the remaining space on the outside of the load-bearing cylinder 1.

[0031] The high-pressure gas cylinder 3 adopts a design with carbon fiber composite material wrapped around an aluminum alloy inner liner to achieve high pressure resistance and lightweight.

[0032] See Figure 4 The gas cylinder support 4 consists of a base 41 and a strip 42. The base 41 provides axial constraint and load-bearing for the high-pressure gas cylinder 3, while the strip 42 provides lateral constraint and load-bearing for the high-pressure gas cylinder 3. The clamping force is adjusted by screws and nuts.

[0033] The base 41 of the gas cylinder support is made of aluminum alloy by machining, and the strips 42 of the gas cylinder support are made of stainless steel sheet. The clamping force is adjusted by screws and nuts to ensure appropriate connection strength and rigidity.

[0034] See Figure 4 The main engine 5 is mounted to the rear end of the propulsion stage via the main engine mounting bracket 6, coaxial with the hull. The main engine mounting bracket 6 consists of a flange 61, a strut 62, and a mounting base 63. The flange 62 connects to the main engine 5, and the mounting base 63 connects to the inner wall of the load-bearing cylinder 1; the strut 62 connects the flange 62 and the mounting base 63, achieving structural connection and load-bearing capacity.

[0035] The flange 61 and mounting base 63 of the main engine mounting bracket 6 can be made of metal and manufactured by machining.

[0036] The strut 62 of the main engine mounting bracket 6 can be made of carbon fiber composite material to ensure strength and rigidity while achieving lightweight.

[0037] Figure 5 This is a schematic diagram of a multi-satellite tandem launch according to an embodiment of the present invention. The propulsion stage 8 is connected to the carrier satellite 9 through the transition section 7, and several carrier satellites 9 are connected in series through the inter-satellite connection device 10. Figure 6 This is a schematic diagram of the transition section 7 and the multi-satellite parallel launch in an embodiment of the present invention. Several carrier satellites 9 are connected in parallel and are connected to the propulsion stage 8 through the transition section 7. The present invention can achieve the launch of two or more satellites with a single rocket by setting up the multi-satellite launch transition section 7.

[0038] The preferred embodiments of the present invention disclosed above are merely illustrative of the invention. These preferred embodiments do not exhaustively describe all details, nor do they limit the invention to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of the invention, thereby enabling those skilled in the art to better understand and utilize the invention. The invention is limited only by the claims and their full scope and equivalents.

[0039] The parts of this invention not described in detail are well-known to those skilled in the art.

Claims

1. A tank-embedded propulsion stage, characterized by, The application relates to a multi-propellant tank embedded propelling stage, which comprises a force-bearing cylinder (1), a propellant tank (2), high-pressure gas cylinders (3), a gas cylinder support (4), a main engine (5) and a main engine mounting support (6); the force-bearing cylinder (1) is provided with uniformly distributed circular ring-shaped tank mounting flanges (11) on the side wall; the propellant tank (2) is embedded in the force-bearing cylinder (1) through the openings of the tank mounting flanges (11) and is connected with the force-bearing cylinder (1) through the tank mounting flanges (11); each high-pressure gas cylinder (3) is mounted at the interval between two adjacent tank mounting flanges (11) through the gas cylinder support (4); the main engine (5) is mounted to the rear end of the propelling stage through the main engine mounting support (6) and is coaxial with the force-bearing cylinder (1); The diameter of the propellant tank (2) is smaller than the opening of the tank mounting flange (11), and the flange (21) of the propellant tank (2) is connected with the tank mounting flange (11) through a hinge hole bolt; The high-pressure gas cylinder (3) adopts an aluminum alloy inner container wound by carbon fiber composite material; The gas cylinder support (4) comprises a base (41) and a strip (42), the base (41) axially restricts and bears the high-pressure gas cylinder (3), and the strip (42) transversely restricts and bears the high-pressure gas cylinder; The main engine mounting support (6) comprises a flange plate (61), a supporting rod (62) and a mounting base (63); the flange plate (62) is used for connecting the main engine (5), the mounting base (63) is connected to the inner wall of the force-bearing cylinder (1), the supporting rod (62) connects the flange plate (62) and the mounting base (63), and the supporting rod (62) is made of carbon fiber composite material; The multi-propellant tank embedded propelling stage realizes one rocket and double or multiple satellite launching by arranging a multi-satellite launching transition section (7).

2. The tank-in- tank propulsive stage according to claim 1, characterized in that, The force-bearing cylinder (1) is cylindrical, the upper end surface is provided with a cabin section butt joint frame (12) for butt joining other cabin sections of a spacecraft, and the lower end surface is provided with a satellite-rocket connecting frame (13) for connecting with a supporting cabin of a carrier rocket.

3. The tank-in- tank propulsive stage according to claim 2, characterized in that, The wall plate (14) of the force-bearing cylinder (1) is welded or screw-connected and formed by machine milling or chemical milling wall plate; the cabin section butt joint frame, the satellite-rocket connecting frame and the tank mounting flange are formed by machining forgings.

4. The tank-in-cell booster stage of claim 1, wherein, The base (41) is made of aluminum alloy by machining.

5. The tank-in-cell booster stage of claim 1 wherein, The strip (42) is made of stainless steel sheet by cutting.

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