CN111891393A - Hybrid propulsion cabin of small high-orbit satellite common platform - Google Patents
Hybrid propulsion cabin of small high-orbit satellite common platform Download PDFInfo
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- CN111891393A CN111891393A CN202010802834.XA CN202010802834A CN111891393A CN 111891393 A CN111891393 A CN 111891393A CN 202010802834 A CN202010802834 A CN 202010802834A CN 111891393 A CN111891393 A CN 111891393A
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- 239000000126 substance Substances 0.000 claims description 75
- 239000000446 fuel Substances 0.000 claims description 17
- 239000007800 oxidant agent Substances 0.000 claims description 17
- 230000001590 oxidative effect Effects 0.000 claims description 15
- 239000002775 capsule Substances 0.000 claims description 8
- 238000012546 transfer Methods 0.000 claims description 8
- 238000005192 partition Methods 0.000 claims description 7
- 239000002828 fuel tank Substances 0.000 claims description 4
- 238000000034 method Methods 0.000 claims description 4
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical group C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- 230000008878 coupling Effects 0.000 claims 3
- 238000010168 coupling process Methods 0.000 claims 3
- 238000005859 coupling reaction Methods 0.000 claims 3
- 238000013461 design Methods 0.000 description 4
- 239000000203 mixture Substances 0.000 description 3
- 238000004891 communication Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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- 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
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- General Physics & Mathematics (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention provides a hybrid propulsion cabin of a small high-orbit satellite common platform, which comprises: the platform cabin main bearing structure is configured to provide an accommodating space, wherein the platform cabin main bearing structure comprises a satellite-rocket connecting ring; a plurality of storage tanks which are arranged in the accommodating space and directly fall on the satellite-rocket connecting ring; and the air path assembly is arranged in the accommodating space, so that the load of the air path assembly is transmitted to the satellite-rocket connecting ring through the platform cabin main bearing structure.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a hybrid propulsion cabin of a small high-orbit satellite public platform.
Background
The satellite has the functions of chemical propulsion and electric propulsion, so that the reliability of the satellite and the flexibility of adapting to various types of tasks are improved to a great extent, and the satellite is one of core technologies of a high-reliability and long-service-life satellite.
More than 50% of domestic and foreign high-orbit communication satellite platforms adopt hybrid propulsion systems, namely, chemical propulsion and electric propulsion are simultaneously configured, such as A2100 platform of Lochhimademadin company, BSS-702MP/HP platform of Boeing company, AlphaBus platform of Tairez, DFH-4/DFH-5 platform of Chinese Oriental Red company and the like, and the hybrid propulsion systems represent the main propulsion technical route of domestic and foreign high-orbit communication satellite platforms. The domestic and foreign satellite platforms are large high-orbit satellite platforms, have wide layout space and bearing margin, and compared with the small high-orbit satellite public platform with greater economic advantages, the composition and layout of the hybrid propulsion cabin of the domestic and foreign satellite platforms face the problem of how to design under the condition of compact space so as to ensure low cost, low mass center and high force transfer characteristic.
Therefore, under the double driving of technology and economy, the composition and layout research of the hybrid propulsion cabin of the small-sized high-orbit satellite public platform is developed, the difficult problems of flexible configuration, high cost performance and high reliability are solved for the small-sized high-orbit satellite public platform, and the hybrid propulsion cabin is very necessary and urgent.
Disclosure of Invention
The invention aims to provide a hybrid propulsion cabin of a small high-orbit satellite common platform, which aims to solve the problem of designing the layout of the hybrid propulsion cabin of the small high-orbit satellite common platform under the condition of compact space.
In order to solve the above technical problem, the present invention provides a hybrid propulsion pod for a small-sized common platform for high-orbit satellites, comprising:
the platform cabin main bearing structure is configured to provide an accommodating space, wherein the platform cabin main bearing structure comprises a satellite-rocket connecting ring;
a plurality of storage tanks which are arranged in the accommodating space and directly fall on the satellite-rocket connecting ring;
and the air path assembly is arranged in the accommodating space, so that the load of the air path assembly is transmitted to the satellite-rocket connecting ring through the platform cabin main bearing structure.
Optionally, in the hybrid propulsion cabin of the small-sized high-orbit satellite common platform, the platform cabin main bearing structure further includes a main bearing truss assembly, + X side plate, -X side plate, + Y side plate, -Y side plate and bottom plate, wherein:
the + X side plate, the-X side plate, the + Y side plate, the-Y side plate and the bottom plate form the accommodating space;
the main bearing truss assembly is positioned in the accommodating space and divides the accommodating space into a plurality of areas;
the main bearing truss assembly supports the + X side plate, the-X side plate, the + Y side plate, the-Y side plate and the bottom plate and transmits the loads of the + X side plate, the-X side plate, the + Y side plate and the-Y side plate to the bottom plate;
the axes of the storage tank and the air path assembly are both vertical to the bottom plate.
Optionally, in the hybrid propulsion cabin of the small-sized high-orbit satellite common platform, the satellite and rocket connecting ring is integrally formed with the bottom plate, the part inside the cabin of the satellite and rocket connecting ring is flush with the surface inside the cabin of the bottom plate, and the part outside the cabin of the satellite and rocket connecting ring protrudes out of the surface outside the cabin of the bottom plate and is connected with the carrying.
Optionally, in the hybrid propulsion cabin of the small-sized high-orbit satellite common platform, the main load-bearing truss component is a carbon fiber truss rod member coated by a honeycomb sandwich plate, and the main load-bearing truss component is directly connected with the part in the cabin of the satellite-rocket connecting ring;
and the load of each side plate and the air path assembly is transmitted to the satellite-rocket connecting ring through the main bearing truss assembly and/or the bottom plate.
Optionally, in the hybrid propulsion cabin of the small-sized common platform for high-orbit satellites, the main force-bearing truss assembly includes a top frame structure and a plurality of internal partition plates integrally formed with the top frame structure, wherein:
the top frame structure is a regular quadrilateral frame, and four sides of the top frame structure are respectively connected with the + X side plate, the-X side plate, the + Y side plate and the-Y side plate to form the accommodating space;
the internal partition board is a thin plate with a square outer contour and is perpendicular to the top frame structure, and the internal partition board intersects with the central point of the accommodating space so as to divide the accommodating space into a plurality of areas;
the bottom edge of the inner partition board close to the central point of the accommodating space is provided with a notch so as to avoid interference with the gas circuit assembly.
Optionally, in the hybrid propulsion pod of the small-scale high-orbit satellite utility platform, the tanks include 2 chemical propulsion fuel tanks, 2 chemical propulsion oxidizer tanks, and 2 electrical propulsion tanks, wherein:
the 2 chemical propulsion fuel storage tanks are respectively arranged in a + X + Y quadrant and a-X-Y quadrant of the accommodating space;
2 chemical propulsion oxidant storage tanks are respectively arranged in a + X-Y quadrant and a-X + Y quadrant of the accommodating space;
the intersection point of the geometric center connecting line of the 2 chemical propulsion fuel storage tanks and the geometric center connecting line of the 2 chemical propulsion oxidant storage tanks is superposed with the central point of the accommodating space in the plane of the bottom plate;
the 2 electric propulsion storage boxes are arranged on an X axis, are respectively close to the + X side plate and the-X side plate, and are symmetrically arranged relative to a Y axis.
Optionally, in the hybrid propulsion cabin of the small-sized common platform for high-orbit satellites, the gas path assembly includes an electric propulsion gas path assembly and 2 chemical propulsion gas cylinders, wherein:
the electric propulsion gas circuit component is arranged at the central position of the inner side of the bottom plate cabin;
the 2 chemical propulsion gas cylinders are respectively placed in a + X + Y quadrant and a-X-Y quadrant of the accommodating space and are respectively positioned in the same area with the 2 chemical propulsion fuel storage tanks;
2 chemical propulsion gas cylinders are directly fastened on the main bearing truss component.
Optionally, in the hybrid propulsion cabin of the small-sized common platform for high-orbit satellites, the hybrid propulsion cabin of the small-sized common platform for high-orbit satellites further includes an orbital transfer chemical thruster, an attitude control chemical thruster, and an electric thruster, wherein:
the method comprises the following steps that 1 set of orbit changing chemical thrusters and 2 sets of attitude control chemical thrusters form a group, and the outer side surfaces of a bottom plate cabin on the + X side and the-X side are respectively provided with a group;
the 2 sets of electric thrusters are arranged side by side to form a group, and the outer side surfaces of the floor cabins on the + Y side and the-Y side are respectively arranged in a group.
Optionally, in the hybrid propulsion capsule of the small-sized common platform for high-orbit satellites, the hybrid propulsion capsule of the small-sized common platform for high-orbit satellites further includes a platform capsule north-south extension structure, where:
the platform cabin north-south expansion structure comprises a + Y expansion side plate, a-Y expansion side plate, a + Y + X expansion side plate, a + Y-X expansion side plate, a-Y + X expansion side plate, a-Y-X expansion side plate, a + Y expansion cover plate and a-Y expansion cover plate;
the platform cabin north-south extension structure and the bottom plate form a closed structure, and various electric single machines and components of the hybrid propulsion cabin are distributed on the inner side of the structure.
Optionally, in the hybrid propulsion cabin of the small-sized high-orbit satellite common platform, the platform cabin main load-carrying structure further includes 4 groups of chemical propulsion storage tank supporting rods and 2 groups of electric propulsion storage tank supporting rods, wherein:
4 groups of chemical propulsion storage tank supporting rods are arranged along the Y axis in an 8 shape, and the chemical propulsion fuel storage tank and the chemical propulsion oxidant storage tank are respectively connected to the main bearing truss component;
and 2 groups of electric propulsion storage box supporting rods are used for respectively connecting the electric propulsion storage box to the main bearing truss component.
In the hybrid propulsion cabin of the small-sized high-orbit satellite common platform, the accommodating space is provided through the platform cabin main bearing structure, the plurality of storage boxes are arranged in the accommodating space and directly fall on the satellite-rocket connecting ring, the gas circuit component is arranged in the accommodating space, and the load is transferred to the satellite-rocket connecting ring through the platform cabin main bearing structure, so that the composition and layout of the small-sized high-orbit satellite common platform hybrid propulsion cabin have the advantages of space compactness, low cost, low mass center, high force transfer characteristic efficiency and the like, the small-sized high-orbit satellite common platform has the advantages of high bearing ratio, high specific rigidity, high specific strength, high reliability, flexibility for adapting to various types of tasks and the like, and the problems of flexible configuration, high cost performance and high reliability are solved for the small-sized high-orbit satellite common platform.
The invention discloses a hybrid propulsion cabin based on a small high-orbit satellite public platform, which is designed under the condition of compact space to ensure low cost, low mass center and high efficiency of force transfer characteristic, so that the problems of flexible configuration, high cost performance and high reliability are solved for the small high-orbit satellite public platform while the satellite configuration layout is reasonable, the force transfer characteristic is high efficiency, the bearing ratio is high, the specific rigidity is high and the specific strength is high.
Drawings
FIG. 1 is a schematic top-view coordinate system of a hybrid propulsion pod for a small high-orbit satellite utility platform according to an embodiment of the present invention;
FIG. 2 is a schematic bottom view of a hybrid propulsion pod of a small high earth orbit satellite utility platform according to an embodiment of the present invention;
FIG. 3 is a schematic side view coordinate system of a hybrid propulsion pod for a small high earth orbit satellite utility platform according to an embodiment of the invention;
fig. 4 is a schematic side-view coordinate system diagram of the main bearing structure of the platform cabin according to an embodiment of the invention;
FIG. 5 is a schematic side view coordinate system of a main bearing structure and a storage box of the platform cabin according to an embodiment of the invention;
fig. 6 is a side view coordinate system schematic diagram of a main force-bearing truss assembly of one embodiment of the invention;
shown in the figure: 1-platform cabin main bearing structure, 2-platform cabin north-south expansion structure, 3-chemical propulsion fuel storage tank, 4-chemical propulsion oxidant storage tank, 5-electric propulsion storage tank, 6-electric propulsion gas circuit component, 7-orbital transfer chemical thruster, 8-attitude control chemical thruster, 9-electric thruster, 10-chemical propulsion gas cylinder, 11-main bearing truss component, 12-satellite-rocket connecting ring, 13- + X side plate, 14-X side plate, 15- + Y side plate, 16-Y side plate, 17-bottom plate, 18-chemical propulsion storage tank supporting rod, 19-electric propulsion storage tank supporting rod, 20- + Y expansion side plate, 21-Y expansion side plate, 22- + Y + X expansion side plate, 23- + Y-X expansion side plate, 24-Y + X expansion side plate, 25-Y-X expansion side plate, 26- + Y expansion cover plate and 27-Y expansion cover plate.
Detailed Description
The hybrid propulsion pod of the small-scale high-orbit satellite common platform according to the present invention will be described in further detail with reference to the accompanying drawings and specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims. It is to be noted that the drawings are in a very simplified form and are not to precise scale, which is merely for the purpose of facilitating and distinctly claiming the embodiments of the present invention.
Furthermore, features from different embodiments of the invention may be combined with each other, unless otherwise indicated. For example, a feature of the second embodiment may be substituted for a corresponding or functionally equivalent or similar feature of the first embodiment, and the resulting embodiments are likewise within the scope of the disclosure or recitation of the present application.
The core idea of the invention is to provide a hybrid propulsion cabin of a small-sized high-orbit satellite common platform, so as to solve the problem of how to design the layout of the hybrid propulsion cabin of the small-sized high-orbit satellite common platform under the condition of compact space.
In order to realize the idea, the invention provides a hybrid propulsion cabin of a small-sized high-orbit satellite common platform, which comprises the following components: the platform cabin main bearing structure is configured to provide an accommodating space, wherein the platform cabin main bearing structure comprises a satellite-rocket connecting ring; a plurality of storage tanks which are arranged in the accommodating space and directly fall on the satellite-rocket connecting ring; and the air path assembly is arranged in the accommodating space, so that the load of the air path assembly is transmitted to the satellite-rocket connecting ring through the platform cabin main bearing structure.
Wherein "drop-off" is to be interpreted as the load of its multiple tanks falling on said satellite-rocket connection rings.
The main structure of the satellite public platform provided by the embodiment is shown in fig. 1, and comprises a platform cabin main bearing structure (1), a platform cabin north-south extension structure (2), a chemical propulsion fuel storage tank (3), a chemical propulsion oxidant storage tank (4), an electrical propulsion storage tank (5), an electrical propulsion gas circuit component (6), an orbital transfer chemical thruster (7), an attitude control chemical thruster (8), an electrical thruster (9) and a chemical propulsion gas cylinder (10). The platform cabin main bearing structure (1) comprises a main bearing truss component (11), a satellite-rocket connecting ring (12), + X side plates (13), + X side plates (14), + Y side plates (15), + Y side plates (16), a bottom plate (17), a chemical propulsion storage tank supporting rod (18) and an electric propulsion storage tank supporting rod (19).
The 4 groups of chemical propulsion storage tank supporting rods (18) provided by the embodiment are arranged in an 8-shaped manner along the north-south direction, and 4 chemical propulsion fuel storage tanks (3) and chemical propulsion oxidant storage tanks (4) are connected to a main bearing truss component (11); 2 groups of electric propulsion storage box supporting rods (19) respectively connect 2 electric propulsion storage boxes (5) to the main bearing truss component (11); 2 chemical propulsion gas cylinders (10) are directly fastened on the main bearing truss component (11).
The orbit-transferring chemical thrusters (7) and the attitude-control chemical thrusters (8) provided by the embodiment are combined into a group, and the groups are respectively arranged outside the cabins of bottom plates (17) on the + X side and the-X side of the satellite; the 2 sets of electric thrusters (9) are arranged side by side to form a group, and the groups are respectively arranged outside the cabins of the bottom plates (17) on the + Y side and the-Y side of the satellite.
The 2 chemical propulsion fuel storage tanks (3) provided by the embodiment are respectively arranged in a + X + Y quadrant and a-X-Y quadrant, and the 2 chemical propulsion oxidant storage tanks (4) are respectively arranged in the + X-Y quadrant and the-X + Y quadrant; the 4 storage tanks are symmetrical relative to the X axis and the Y axis of the layout coordinate system, namely the intersection point of the connecting line of the geometric centers of the 2 chemical propulsion fuel storage tanks (3) and the connecting line of the geometric centers of the 2 chemical propulsion oxidant storage tanks (4) is coincided with the original point O of the layout coordinate system in an XOY plane; 2 chemical propulsion gas cylinders (10) are respectively distributed in a + X + Y quadrant and a-X-Y quadrant and are respectively positioned in the same area with the 2 chemical propulsion fuel storage tanks (3); the 2 electric propulsion storage boxes (5) are arranged on the X axis, are respectively close to the + X side plate (13) and the-X side plate (14) and are symmetrically arranged relative to the Y axis. The axes of all the storage tanks and the air cylinders are vertical to the XOY plane.
The platform cabin north-south extension structure (2) provided by the embodiment comprises + Y extension side plates (20), -Y extension side plates (21), + Y + X extension side plates (22), + Y-X extension side plates (23), -Y + X extension side plates (24), -Y-X extension side plates (25), + Y extension cover plates (26), and-Y extension cover plates (27), wherein the platform cabin north-south extension structure (2) and the bottom plate (17) form a closed structure, and various electric units and components of a hybrid propulsion cabin are distributed on the inner side of the structure.
The design concept of tiling all the gas cylinders of the storage tank is adopted in the embodiment, the design with low cost, low mass center and high force transmission characteristic is provided under the condition of compact space, and the problems of flexible configuration, high cost performance and high reliability are solved for a small high-orbit satellite common platform.
In one embodiment of the invention, the satellite-rocket connecting ring (12) is integrally formed with the bottom plate (17), the cabin inner part of the satellite-rocket connecting ring is flush with the cabin inner side surface of the bottom plate (17), and the cabin outer part of the satellite-rocket connecting ring protrudes out of the bottom plate (17) to be connected with a carrier; the main bearing truss component (11) is reinforced by coating a carbon fiber truss rod with a honeycomb sandwich plate and is directly connected with the cabin interior part of the satellite-rocket connecting ring (12); the loads of the side plates and the bottom plate (17) are transmitted to the satellite-rocket connecting ring (12) through the main bearing truss assembly (11) and the bottom plate (17), wherein the chemical propulsion fuel storage tank (3), the chemical propulsion oxidant storage tank (4) and the electric propulsion storage tank (5) are directly loaded on the satellite-rocket connecting ring (12), and the electric propulsion gas circuit assembly (6) is installed on the inner side of the cabin of the bottom plate (17).
In one embodiment of the invention, 4 groups of chemical propulsion tank supporting rods (18) are arranged in an 8-shaped manner along the north-south direction, and 4 chemical propulsion fuel tanks (3) and chemical propulsion oxidant tanks (4) are connected to a main bearing truss component (11); 2 groups of electric propulsion storage box supporting rods (19) respectively connect 2 electric propulsion storage boxes (5) to the main bearing truss component (11); 2 chemical propulsion gas cylinders (10) are directly fastened on the main bearing truss component (11).
In one embodiment of the invention, 1 set of orbit-changing chemical thrusters (7) and 2 sets of attitude-control chemical thrusters (8) form a group, and the groups are respectively arranged on the outer surfaces of cabins of bottom plates (17) on the + X side and the-X side of a satellite; the 2 sets of electric thrusters (9) are arranged side by side to form a group, and the groups are respectively arranged outside the cabins of the bottom plates (17) on the + Y side and the-Y side of the satellite.
In one embodiment of the invention, 2 chemical propellant fuel tanks (3) are respectively arranged in the + X + Y quadrant and the-X-Y quadrant, and 2 chemical propellant oxidant tanks (4) are respectively arranged in the + X-Y quadrant and the-X + Y quadrant; the 4 storage tanks are symmetrical relative to the X axis and the Y axis of the layout coordinate system, namely the intersection point of the connecting line of the geometric centers of the 2 chemical propulsion fuel storage tanks (3) and the connecting line of the geometric centers of the 2 chemical propulsion oxidant storage tanks (4) is coincided with the original point O of the layout coordinate system in an XOY plane; 2 chemical propulsion gas cylinders (10) are respectively distributed in a + X + Y quadrant and a-X-Y quadrant and are respectively positioned in the same area with the 2 chemical propulsion fuel storage tanks (3); the 2 electric propulsion storage boxes (5) are arranged on the X axis, are respectively close to the + X side plate (13) and the-X side plate (14) and are symmetrically arranged relative to the Y axis. The axes of all the storage tanks and the air cylinders are vertical to the XOY plane.
In one embodiment of the invention, the platform cabin north-south extension structure (2) comprises a + Y extension side plate (20), -Y extension side plate (21), + Y + X extension side plate (22), + Y-X extension side plate (23), -Y + X extension side plate (24), -Y-X extension side plate (25), + Y extension cover plate (26), -Y extension cover plate (27), the platform cabin north-south extension structure (2) and the bottom plate (17) form a closed structure, and various types of electric units and components of the hybrid propulsion cabin are arranged inside the structure.
In summary, the above embodiments have described in detail different configurations of the hybrid propulsion pod of the small-scale high-orbit satellite common platform, and it is understood that the present invention includes, but is not limited to, the configurations listed in the above embodiments, and any modifications made on the configurations provided by the above embodiments are within the scope of the present invention. One skilled in the art can take the contents of the above embodiments to take a counter-measure.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. For the system disclosed by the embodiment, the description is relatively simple because the system corresponds to the method disclosed by the embodiment, and the relevant points can be referred to the method part for description.
The above description is only for the purpose of describing the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention, and any variations and modifications made by those skilled in the art based on the above disclosure are within the scope of the appended claims.
Claims (10)
1. A hybrid propulsion pod for a small, high earth orbit satellite utility platform, comprising:
the platform cabin main bearing structure is configured to provide an accommodating space, wherein the platform cabin main bearing structure comprises a satellite-rocket connecting ring;
a plurality of storage tanks which are arranged in the accommodating space and directly fall on the satellite-rocket connecting ring;
and the air path assembly is arranged in the accommodating space, so that the load of the air path assembly is transmitted to the satellite-rocket connecting ring through the platform cabin main bearing structure.
2. The hybrid propulsion capsule for small high orbit satellite utility platforms of claim 1, wherein the platform capsule primary messenger structure further comprises a primary messenger truss assembly, + X side panel, -X side panel, + Y side panel, -Y side panel, and a bottom panel, wherein:
the + X side plate, the-X side plate, the + Y side plate, the-Y side plate and the bottom plate form the accommodating space;
the main bearing truss assembly is positioned in the accommodating space and divides the accommodating space into a plurality of areas;
the main bearing truss assembly supports the + X side plate, the-X side plate, the + Y side plate, the-Y side plate and the bottom plate and transmits the loads of the + X side plate, the-X side plate, the + Y side plate and the-Y side plate to the bottom plate;
the axes of the storage tank and the air path assembly are both vertical to the bottom plate.
3. A hybrid propulsion chamber for a small high-orbit satellite utility platform as claimed in claim 2, wherein the satellite-rocket coupling ring is integrally formed with the base plate, the inboard portion of the satellite-rocket coupling ring is flush with the inboard surface of the base plate, and the outboard portion of the satellite-rocket coupling ring protrudes from the outboard surface of the base plate and is connected to the vehicle.
4. The hybrid propulsion capsule of a small-scale high-orbit satellite common platform according to claim 3, wherein the main force-bearing truss component is a carbon fiber truss rod member coated by a honeycomb sandwich plate, and the main force-bearing truss component is directly connected with the inboard part of the satellite-rocket connecting ring;
and the load of each side plate and the air path assembly is transmitted to the satellite-rocket connecting ring through the main bearing truss assembly and/or the bottom plate.
5. The hybrid propulsion pod of a small high-orbit satellite utility platform of claim 4, wherein the primary, force-bearing truss assembly comprises a top frame structure, a plurality of internal bulkheads integrally formed with the top frame structure, wherein:
the top frame structure is a regular quadrilateral frame, and four sides of the top frame structure are respectively connected with the + X side plate, the-X side plate, the + Y side plate and the-Y side plate to form the accommodating space;
the internal partition board is a thin plate with a square outer contour and is perpendicular to the top frame structure, and the internal partition board intersects with the central point of the accommodating space so as to divide the accommodating space into a plurality of areas;
the bottom edge of the inner partition board close to the central point of the accommodating space is provided with a notch so as to avoid interference with the gas circuit assembly.
6. The hybrid propulsion pod of a small high-earth-orbit satellite utility platform of claim 5, wherein the tanks comprise 2 chemical propulsion fuel tanks, 2 chemical propulsion oxidizer tanks, and 2 electrical propulsion tanks, wherein:
the 2 chemical propulsion fuel storage tanks are respectively arranged in a + X + Y quadrant and a-X-Y quadrant of the accommodating space;
2 chemical propulsion oxidant storage tanks are respectively arranged in a + X-Y quadrant and a-X + Y quadrant of the accommodating space;
the intersection point of the geometric center connecting line of the 2 chemical propulsion fuel storage tanks and the geometric center connecting line of the 2 chemical propulsion oxidant storage tanks is superposed with the central point of the accommodating space in the plane of the bottom plate;
the 2 electric propulsion storage boxes are arranged on an X axis, are respectively close to the + X side plate and the-X side plate, and are symmetrically arranged relative to a Y axis.
7. A hybrid propulsion pod for a small, high orbit satellite utility platform as claimed in claim 6 wherein the gas circuit assembly comprises an electric propulsion gas circuit assembly and 2 chemical propulsion gas cylinders, wherein:
the electric propulsion gas circuit component is arranged at the central position of the inner side of the bottom plate cabin;
the 2 chemical propulsion gas cylinders are respectively placed in a + X + Y quadrant and a-X-Y quadrant of the accommodating space and are respectively positioned in the same area with the 2 chemical propulsion fuel storage tanks;
2 chemical propulsion gas cylinders are directly fastened on the main bearing truss component.
8. The hybrid propulsion pod of a small-scale, high-orbit satellite utility platform of claim 3, further comprising an orbital transfer chemical thruster, an attitude control chemical thruster, and an electric thruster, wherein:
the method comprises the following steps that 1 set of orbit changing chemical thrusters and 2 sets of attitude control chemical thrusters form a group, and the outer side surfaces of a bottom plate cabin on the + X side and the-X side are respectively provided with a group;
the 2 sets of electric thrusters are arranged side by side to form a group, and the outer side surfaces of the floor cabins on the + Y side and the-Y side are respectively arranged in a group.
9. The hybrid propulsion capsule for a small-scale, high-orbit satellite utility platform of claim 2, further comprising a platform capsule north-south extension structure, wherein:
the platform cabin north-south expansion structure comprises a + Y expansion side plate, a-Y expansion side plate, a + Y + X expansion side plate, a + Y-X expansion side plate, a-Y + X expansion side plate, a-Y-X expansion side plate, a + Y expansion cover plate and a-Y expansion cover plate;
the platform cabin north-south extension structure and the bottom plate form a closed structure, and various electric single machines and components of the hybrid propulsion cabin are distributed on the inner side of the structure.
10. The hybrid propulsion vessel of a small high orbit satellite utility platform of claim 2, wherein the platform vessel primary load-bearing structure further comprises 4 sets of chemically-propelled tank support rods and 2 sets of electrically-propelled tank support rods, wherein:
4 groups of chemical propulsion storage tank supporting rods are arranged along the Y axis in an 8 shape, and the chemical propulsion fuel storage tank and the chemical propulsion oxidant storage tank are respectively connected to the main bearing truss component;
and 2 groups of electric propulsion storage box supporting rods are used for respectively connecting the electric propulsion storage box to the main bearing truss component.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210126570.XA CN114379825B (en) | 2020-08-11 | 2020-08-11 | Small-sized high-orbit satellite public platform propulsion system |
| CN202010802834.XA CN111891393B (en) | 2020-08-11 | 2020-08-11 | Hybrid propulsion cabin of small high-orbit satellite common platform |
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| CN112977882A (en) * | 2021-03-12 | 2021-06-18 | 上海卫星工程研究所 | High orbit satellite platform structure with central force bearing cylinder type storage boxes tiled in parallel |
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| CN115743602A (en) * | 2022-09-28 | 2023-03-07 | 北京微纳星空科技有限公司 | Satellite platform |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111891393B (en) | 2022-03-15 |
| CN114379825B (en) | 2023-07-14 |
| CN114379825A (en) | 2022-04-22 |
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