CN116853530A - Storage tank embedded type propulsion stage - Google Patents
Storage tank embedded type propulsion stage Download PDFInfo
- 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
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- China
- Prior art keywords
- storage tank
- tank
- cylinder
- propulsion stage
- main engine
- 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
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- 238000003860 storage Methods 0.000 title claims abstract description 48
- 239000003380 propellant Substances 0.000 claims abstract description 26
- 230000007704 transition Effects 0.000 claims description 8
- 210000001503 joint Anatomy 0.000 claims description 7
- 229910000838 Al alloy Inorganic materials 0.000 claims description 6
- 239000002131 composite material Substances 0.000 claims description 6
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 5
- 239000004917 carbon fiber Substances 0.000 claims description 5
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 5
- 238000005242 forging Methods 0.000 claims description 3
- 239000010935 stainless steel Substances 0.000 claims description 3
- 229910001220 stainless steel Inorganic materials 0.000 claims description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims 1
- 229910052799 carbon Inorganic materials 0.000 claims 1
- 239000000835 fiber Substances 0.000 claims 1
- 238000009434 installation Methods 0.000 abstract description 7
- 238000010586 diagram Methods 0.000 description 5
- 238000003801 milling Methods 0.000 description 4
- 230000000452 restraining effect Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000010008 shearing Methods 0.000 description 3
- 238000003754 machining Methods 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant 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
Technical Field
The invention relates to a propulsion-stage configuration which is mainly applied to the orbit transfer of a medium-high orbit satellite.
Background
Due to the need for orbital or orbital maneuvers, high and medium orbit satellites, deep space exploration vehicles and other spacecraft are typically equipped with high thrust main engines for orbit control and need to carry large amounts of propellants, the total weight of which is even more than 50% of the total spacecraft. The dry weight of the storage tank, the pipeline valve path and the like caused by the dry weight becomes 'heavy' after the spacecraft is in orbit, and extra propellant waste is caused in the follow-up orbit change. Therefore, an independent upper stage or propulsion stage can be adopted, the orbit is separated and discarded after being completed, and the structure and the weight of the spacecraft for performing the task on orbit are optimized. For such upper or propulsion stages, however, the huge amount of propellant carrying requirements results in an increase in the size and number of propellant tanks, which tends to result in an increase in the size of the propulsion stage of the spacecraft. The limited envelope of the fairing of the launch vehicle and the limit of the launch weight form a very outstanding contradiction.
Conventional aircraft employ a center load barrel or outer load barrel configuration: the propellant storage tanks are generally arranged inside the central bearing cylinder, the mass center is raised, the quantity of the storage tanks is limited (generally 2), and a few satellites in a central bearing cylinder configuration are paved on a box plate structure outside the central bearing cylinder by adopting 4 storage tanks, so that the requirements of the carrying quantity of the propellant are met, the layout space of instruments and equipment is occupied, and meanwhile, the space inside the central bearing cylinder is wasted; although the outer bearing cylinder structure can realize that a plurality of storage tanks are tiled into a module for installation, the structural size and the weight are increased, and the compact structure layout envelope and the light weight requirement are difficult to consider under the condition of a large amount of propellant requirements.
Disclosure of Invention
The technical problems to be solved by the invention are as follows: the invention provides an embedded propulsion stage of a storage tank, which realizes the installation of a large-capacity propellant storage tank and simultaneously realizes simple structural form, compact layout and lighter total weight.
The technical scheme adopted by the invention is as follows: the embedded propulsion level of the storage tank 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; 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.
Furthermore, the bearing cylinder is cylindrical, and the upper end surface is provided with a cabin section butt joint frame for butt joint of other cabin sections of the spacecraft; the lower end face is provided with a satellite-rocket connecting frame which is used for being connected with a carrier rocket supporting cabin.
Further, the wall plate of the bearing cylinder is welded or screwed by adopting a machine milling or chemical milling wall plate; the cabin butt joint frame, the satellite and arrow connecting frame and the storage box mounting flange are formed by forging machine.
Further, the diameter of the propulsion-stage storage tank is smaller than the opening of the mounting flange of the storage tank, and the flange of the propulsion-stage storage tank is connected with the mounting flange of the storage tank through a hinged hole bolt.
Furthermore, the high-pressure gas cylinder is made of carbon fiber composite materials and is wound on the aluminum alloy liner.
Further, the gas cylinder support comprises a base and a strip, the base is used for axially restraining and bearing the high-pressure gas cylinder, and the strip is used for transversely restraining and bearing the high-pressure gas cylinder.
Further, the base is manufactured by adopting an aluminum alloy machining process.
Further, the strip is cut from stainless steel sheet.
Further, the main engine mounting bracket comprises a flange plate, a stay bar and a mounting seat; the flange plate is used for connecting the main engine, the mounting seat is connected to the inner wall of the bearing cylinder, the stay bar is connected with the flange plate and the mounting seat, and the stay bar is made of carbon fiber composite materials.
Furthermore, the embedded propulsion stage of the storage tank realizes one-arrow double-star or multi-star emission by arranging a multi-star emission transition section.
Compared with the prior art, the invention has the following beneficial effects:
(1) The propulsion stage adopts a large-volume storage tank embedded type bearing cylinder configuration, and is particularly suitable for tasks with smaller envelope of the fairing of the carrier rocket and more requirements on the carrying capacity of the propellant of the spacecraft. The high-capacity propellant can be carried, the large speed increment required by track transfer is provided, and the high-capacity propellant has the characteristics of compact structure, light weight and high bearing capacity.
(2) The embedded propulsion level of the storage tank realizes the installation of the large-capacity propellant storage tank and simultaneously realizes the simple structure, compact layout and lighter total weight. The storage tank embedded propulsion level can be applied to spacecrafts such as satellites, freight spacecraft, deep space exploration aircraft and the like, and can provide large speed increment under the condition of meeting the envelope constraint of a small carrier rocket fairing. Meanwhile, the invention can realize multi-star serial and parallel emission by adding the transition section.
Drawings
FIG. 1 is a schematic view of the general configuration and composition of an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a force-bearing cylinder according to an embodiment of the present invention;
FIG. 3 is a schematic illustration of the installation of a propellant reservoir according to an embodiment of the present invention;
FIG. 4 is a schematic view of the installation of a high pressure cylinder and cylinder bracket and a main engine and main engine mounting bracket according to an embodiment of the present invention;
FIG. 5 is a schematic diagram of a multi-star tandem carrier emission of an embodiment of the present invention;
fig. 6 is a schematic diagram of a transition section and multi-star parallel bearer emission according to an embodiment of the present invention.
Detailed Description
The embodiment is implemented on the premise of taking the technical scheme of the invention as a premise, and a detailed implementation mode and a specific operation process are provided, but the protection scope of the invention is not limited to the following embodiment, and a person skilled in the art can modify and color the embodiment without changing the spirit and content of the invention.
Fig. 1 is an exploded view of the system components of an embodiment of the present invention. A storage tank embedded propulsion stage 8 comprises a bearing cylinder 1, a propellant storage tank 2, a high-pressure gas cylinder 3, a gas cylinder bracket 4, a main engine 5 and a main engine mounting bracket 6. The bearing cylinder 1 is a supporting structure of the whole cabin body, adopts a cylindrical bearing cylinder configuration, and has good overall rigidity and bearing capacity. The side wall of the bearing cylinder 1 is uniformly provided with 4 circular tank mounting flanges 11 with large openings, and the propellant tank 2 is embedded into the bearing cylinder 1 through the openings of the flanges and is connected through the tank mounting flanges 11. The high-pressure gas cylinder 3 is mounted to the bearing cylinder 1 at intervals of 4 storage tank mounting flanges 11 through a gas cylinder bracket 4. The main engine 5 is mounted to the rear end of the propulsion stage by a main engine mounting bracket 6, coaxial with the spacecraft cabin.
Referring to fig. 2, the force bearing cartridge 1 includes: the upper end face is a cabin butt joint frame 12 which is used for butt joint installation with other cabin sections of the spacecraft; the lower end face is a satellite-rocket connecting frame 13 which is used for being connected with a carrier rocket supporting cabin, and a belting or point type connecting mode can be selected according to task requirements; a tank mounting flange 11 with 4 evenly distributed circumferential directions and a bearing cylinder wall plate 14. Wherein the tank mounting flange 11 is provided with a large-diameter round hole, and the diameter of the round hole is larger than that of the propellant tank 2, so that the propellant tank 2 is embedded into the bearing cylinder 1. The wall plates 14 of the whole bearing cylinder 1 can be formed by adopting a machine milling or chemical milling wall plate to carry out welding or screwing process. The cabin section butt joint frame, the satellite and arrow connecting frame and the storage box mounting flange can be formed by adopting forging machine processing.
The geometric center of the propellant reservoir 2 should be located at the center plane of the thickness of the wall of the barrel 1.
Referring to fig. 3, the flange 21 of the propellant reservoir 2 is connected to the reservoir mounting flange 11 of the cartridge 1 by means of connecting bolts 22.
The connecting bolt 22 is a hinged hole bolt, and can bear the shearing load in the flying direction generated in the process of launching the storage tank more than a common bolt. Of course, the bearing of the shearing force can be realized by adopting structures such as a shearing-resistant taper sleeve, a load-reducing pin and the like according to actual needs.
Referring to fig. 4, the high-pressure gas cylinder 3 is mounted to the bearing cylinder 1 at intervals of the 4 tank mounting flanges 11 through the gas cylinder bracket 4, and the outer residual space of the bearing cylinder 1 is just utilized.
The high-pressure gas cylinder 3 adopts a design that a carbon fiber composite material is wound on an aluminum alloy liner, so as to realize high pressure bearing and light weight.
Referring to fig. 4, the gas cylinder support 4 is composed of a base 41 and a strip 42, the base 41 is used for axially restraining and bearing the high-pressure gas cylinder 3, the strip 42 is used for transversely restraining and bearing the high-pressure gas cylinder 3, and the tightening force is adjusted through screws and nuts.
The base 41 of the gas cylinder support 4 is manufactured by adopting an aluminum alloy machine, the strip 42 of the gas cylinder support 4 is cut by adopting stainless steel sheets, and the tightening force is adjusted by screws and nuts, so that proper connection strength and rigidity are ensured.
Referring to fig. 4, a main engine 5 is mounted to the rear end of the propulsion stage by a main engine mounting bracket 6, coaxial with the nacelle. The main engine mounting bracket 6 is composed of a flange plate 61, a stay bar 62 and a mounting seat 63. Wherein, the flange plate 62 is used for connecting the main engine 5, and the mounting seat 63 is used for connecting to the inner wall of the bearing cylinder 1; the stay bar 62 connects the flange plate 62 with the mounting seat 63 to realize structural connection and bearing.
The flange 61 and the mount 63 of the main engine mount 6 may be made of a metallic material by machining.
The stay bar 62 of the main engine mounting bracket 6 can be made of carbon fiber composite material, so that the strength and the rigidity are ensured, and the weight is reduced.
FIG. 5 is a schematic diagram of a multi-star serial carrier emission of an embodiment of the present invention, where a propulsion stage 8 is connected to carrier satellites 9 through transition sections 7, and several carrier satellites 9 are connected in series through inter-satellite connection means 10; fig. 6 is a schematic diagram of a transition section 7 and a multi-star parallel carrier emission of an embodiment of the present invention, where several carrier stars 9 are connected in parallel, and a propulsion stage 8 is connected through the transition section 7. The invention can realize double-star and multi-star launching of one arrow by arranging the multi-star launching transition section 7.
The preferred embodiments of the invention disclosed above are intended only to assist in the explanation of the invention. The preferred embodiments are not exhaustive or to limit the invention to the precise form disclosed. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best understand and utilize the invention. The invention is limited only by the claims and the full scope and equivalents thereof.
The invention, in part not described in detail, is within the skill of those skilled in the art.
Claims (10)
1. The embedded propulsion level of the storage tank is characterized by comprising a bearing cylinder (1), a propellant storage tank (2), a high-pressure gas cylinder (3), a gas cylinder bracket (4), a main engine (5) and a main engine mounting bracket (6); a circular storage tank mounting flange (11) is uniformly distributed on the side wall of the bearing cylinder (1); the propellant storage tank (2) is embedded into the bearing cylinder (1) through an opening of the storage tank mounting flange (11) and is connected with the bearing cylinder (1) through the storage tank mounting flange (11); each high-pressure gas cylinder (3) is respectively arranged at the interval between two adjacent storage tank mounting flanges (11) through a gas cylinder bracket (4); the main engine (5) is mounted to the rear end of the propulsion stage through a main engine mounting bracket (6) and is coaxial with the bearing cylinder (1).
2. The tank embedded propulsion stage according to claim 1, wherein the force-bearing cylinder (1) is cylindrical, and a cabin section butt frame (12) is arranged on the upper end surface and is used for butt-jointing other cabin sections of the spacecraft; the lower end face is provided with a satellite-rocket connecting frame (13) which is used for being connected with a carrier rocket supporting cabin.
3. The tank-embedded propulsion stage according to claim 2, characterized in that the wall plate (14) of the force-bearing cartridge (1) is welded or screwed with a machine-milled or chemically-milled wall plate; the cabin butt joint frame, the satellite and arrow connecting frame and the storage box mounting flange are formed by forging machine.
4. Tank in-line 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 that the flange (21) of the propulsion stage tank (2) is connected to the tank mounting flange (11) by means of a hinged hole bolt.
5. Tank-embedded propulsion stage according to claim 1, characterized in that the high-pressure gas cylinder (3) is wound with an aluminium alloy liner using carbon fibre composite material.
6. Tank-embedded propulsion stage according to claim 1, characterized in that the cylinder support (4) comprises a base (41) and a strip (42), the base (41) axially constraining and carrying the high-pressure cylinder (3), the strip (42) laterally constraining and carrying the high-pressure cylinder.
7. Tank in-line propulsion stage according to claim 6, characterized in that said base (41) is machined from an aluminium alloy.
8. The tank in-line propulsion stage according to claim 6, characterized in that said strips (42) are cut out of stainless steel sheet.
9. Tank in-line propulsion stage according to claim 1, characterized in that the main engine mounting bracket (6) comprises a flange (61), a stay (62) and a mounting seat (63); the flange plate (62) is used for connecting the main engine (5), the mounting seat (63) is connected to the inner wall of the bearing cylinder (1), the support rod (62) is connected with the flange plate (62) and the mounting seat (63), and the support rod (62) is made of carbon fiber composite materials.
10. The tank in-line propulsion stage according to claim 1, characterized in that it implements a double or multiple star launch by providing a multiple star launch transition (7).
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) |
-
2023
- 2023-06-30 CN CN202310794483.6A patent/CN116853530A/en active Pending
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