CN102303710B - General propelling module for small satellites - Google Patents
General propelling module for small satellites Download PDFInfo
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- CN102303710B CN102303710B CN 201110152846 CN201110152846A CN102303710B CN 102303710 B CN102303710 B CN 102303710B CN 201110152846 CN201110152846 CN 201110152846 CN 201110152846 A CN201110152846 A CN 201110152846A CN 102303710 B CN102303710 B CN 102303710B
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Abstract
The invention discloses a general propelling module for small satellites. The propelling module comprises an upper flange, a lower flange, a storage box bracket, an engine bracket and a shell, wherein the upper flange and the lower flange are positioned on two end faces of the shell respectively, the upper flange is connected with an electronic compartment, and the lower flange is a satellite arrow butted face. The shell has a hollow round table-shaped structure consisting of a purlin structure and is provided with an aluminum envelope, and the storage box bracket is positioned at the lower part of the inside middle part of the shell. The storage box bracket has a cover-like structure, the upper surface of which is smooth and the lower surface of which is provided with reinforcing ribs; the center of the storage box bracket is provided with an ion propeller pipeline outlet; the storage box bracket is provided with bottleneck mounting holes at the quadrants of the Y axis and the Z axis of the YOZ plane of a propelling module body coordinate system and in the direction forming 45-degree angles with the coordinate axes; and the upper surface of the storage box bracket is a mounting surface for spreading equipment and pipelines. An engine bracket is respectively arranged at four intersection points of the shell and the Y axis and the Z axis of the propelling module body coordinate system, wherein the brackets at the two intersection points of the shell and the Y axis are positively arranged engine brackets, and the brackets at the two intersection points of the shell and the Z axis are obliquely arranged engine brackets.
Description
Technical field
The present invention relates to a kind of satellite booster cabin.
Background technology
Along with the development that small satellite is used, the small satellite function is constantly strengthened, and system also becomes increasingly complex.In order to satisfy the needs of the long-term attitude and orbit control in orbit of small satellite, small satellite need carry more fuel or adopt electric propulsion as the rail control engine of small satellite.Simultaneously, along with the shortening of small satellite lead time, also need the part development of satellite and experimental work to walk abreast and carry out, to optimize the development flow process, the quickening Development Schedule.
If adopt conventional satellite configuration, small satellite propulsion system and other electronic machine are installed in the same cabin, owing to be subjected to the impact in celestial body space, the portable fuel of small satellite will be restricted, the driving engine plume can cause certain influence to sensor on the star simultaneously, and it is larger to affect meeting when making the electricity consumption thruster.In addition, because propulsion system and other electronic machine are installed in the same cabin, the work such as the installation of propulsion system equipment, accurate measurement, leak detection will take the main line of satellite development, prolong the lead time of small satellite.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, a kind of General propelling module for small satellites that holds two propulsion systems is provided, can so that small satellite carries more fuel, can reduce the complexity of satellite layout and general assembly operation simultaneously.
Technical solution of the present invention is: General propelling module for small satellites comprises upper flange, lower flange, storage tank support, engine bed and housing; Upper flange and lower flange lay respectively on two end faces of housing, and upper flange is connected with electronic compartment, and lower flange is the satellite-rocket docking face; Housing is the truncated cone-shaped structure of hollow, and the inboard that the storage tank support is positioned at housing is the position on the lower side; The storage tank support is the lid-like that upper surface is smooth, lower surface is furnished with reinforced rib, the center of described lid-like has ion thruster pipeline outlet, the storage tank support propulsion module body coordinate system YOZ plane-Y-axis and-Z axis place quadrant and coordinate axle direction position at 45 ° has hydrazine bottle mounting hole; The upper surface of storage tank support is the attachment face that equipment Pipe-Line is laid; Housing with four intersection point places propulsion module body coordinate system Y-axis and Z axis an engine bed is housed respectively, wherein the support with two intersection point places of Y-axis is the formal dress engine bed, with the support at two intersection point places of Z axis be the angle mount engine bed, the formal dress engine bed is parallel with the Y-axis of propulsion module along the engine mounting face of Z-direction, and the angle mount engine bed becomes 15 ° of angles along the engine mounting face of Y direction with the Z axis of propulsion module; The origin of coordinates O of described propulsion module body coordinate system is at the theoretical center of described satellite-rocket docking face, X-axis is pointed to the direction of upper flange along origin of coordinates O, Z axis crosses origin of coordinates O and perpendicular to X-axis, Z axis is directed towards ground under whole star state of flight, and Y-axis becomes right-handed system with Z axis, Y-axis.
The angle of the side of described truncated cone-shaped structure and satellite-rocket docking face is 83.8 °.On the described storage tank support pull bar is housed, an end of pull bar is connected with the storage tank support, and the other end of pull bar is connected with upper flange.The outside of described housing is provided with strut, and an end of strut is connected on the housing, and the other end of strut is connected on the base plate of electronic compartment.On the described housing and four intersection point places propulsion module body coordinate system Y-axis and Z axis respectively leave two engine pipelines perforation.On the described housing with-Z-direction angle be that 45 ° direction respectively leaves kidney-shaped cable penetrating hole, a place near the position at upper flange 150mm place.In the described propulsion module body coordinate system YOZ plane-Z axis partially+30 ° of directions of Y-axis and+Z axis partially+intersection of 60 ° of directions of Y-axis and housing adds the valve mounting hole apart from the satellite and the rocket to what 230mm place in interface had respectively an electric propulsion system.In the described propulsion module body coordinate system YOZ plane-Z axis partially+intersection of 45 ° of directions of Y-axis and housing has the mounting hole of hydrazine gas fill valve to interface 230mm place apart from the satellite and the rocket.In the described propulsion module body coordinate system YOZ plane+Z axis partially-intersection of 45 ° of directions of Y-axis and housing has the mounting hole of hydrazine liquid fill valve to interface 132mm place apart from the satellite and the rocket.The upper surface of described storage tank support is 40mm apart from the axis height of engine bed, apart from satellite and the rocket interface 190mm.
The present invention's advantage compared with prior art is:
(1) propulsion module of the present invention can be installed a cover hydrazine propulsion system and a cover electric propulsion system simultaneously, can be so that small satellite carries more fuel, satisfy repeatedly orbital transfer needs of satellite, simultaneously can overcome the driving engine plume to the impact of sensor on the star, so that electric thruster becomes possibility as the rail control engine of small satellite;
(2) adopt independent propulsion module form can at utmost increase the distance of sensor on driving engine and the star, reduce the plume impact, electronic compartment and propulsion module carry out simultaneously as two main lines simultaneously, propulsion module can independently carry out the work such as general assembly, test, optimized the development flow process of satellite, reduce the complexity of satellite layout and general assembly operation, shorten the satellite lead time;
(3) propulsion system is arranged separately in the propulsion module, and pipeline welding space is abundant, handled easily, and simple, safety are implemented in general assembly.
Description of drawings
Fig. 1 is the integral structure figure of propulsion module of the present invention;
Fig. 2 is the front view of propulsion module of the present invention;
Fig. 3 is the A-A cutaway view of propulsion module among Fig. 2.
The specific embodiment
As shown in Figure 1, propulsion module of the present invention mainly is comprised of propulsion module main body and storage tank support 2 two parts, and wherein the propulsion module main body is divided into again upper flange 1, lower flange 4, housing 3 three parts.In order to narrate conveniently, the body coordinate system (O-XYZ) that at first defines propulsion module is as follows:
Origin of coordinates O: the theoretical center of propulsion module lower flange 4 places, satellite and the rocket burbling area; X-axis: upper flange 1 direction of pointing to propulsion module along the origin of coordinates; Z axis: cross the origin of coordinates and perpendicular to X-axis, directed towards ground under the state of flight; Y-axis: become right-handed system with Z, Y-axis.
As shown in Figure 1 and Figure 2, propulsion module docks with the satellite electron cabin by upper flange 1, and upper flange 1 is the circular ring structure that a side has flanging, is evenly equipped with through hole on the flanging and is used for being connected with electronic compartment.Also be provided with in addition two pin holes on the upper flange 1, to guarantee the repetition setting accuracy of propulsion module and electronic compartment.Lower flange 4 is the butt joint ring of satellite and delivery, according to the delivery docking type spectrum of selecting, can select difform lower flange 4 to mate with it.
Storage tank support 2 is the main load bearing component of propulsion module, and the inboard that is positioned at housing 3 is the position on the lower side, is lid-like.Housing 3 adds lead-covering for the truncated cone-shaped structure of the hollow that the stringer structure forms.Storage tank support 2 is at the circle centre position opening, and this opening is the outlet of ion thruster pipeline.Storage tank support 2 edges the YOZ plane-Y-axis and-have gap, the operational observations mouth when this gap is the Piezoelectric switches crossing cabin in the quadrant of Z axis place.Storage tank support 2 the YOZ plane-Y-axis and-Z axis place quadrant and coordinate axle direction at 45 ° has through hole, this through hole is hydrazine bottle mounting hole.The form of storage tank support 2 is the configuration of two propulsion systems (hydrazine advances and electric propulsion) when installing simultaneously, if hydrazine advances when installing separately, the center culvert opening can or reduce according to the modification of 5N driving engine interface shape, and increases through hole so that the hydrazine bottle to be installed according to system requirements in hydrazine bottle mounting hole symmetric position.In addition, can be according to the equipment situation at 2 cancellations of storage tank support or the equipment of adjustment mounting hole.The upper surface of storage tank support 2 is attachment faces of major equipment and pipe installation, and surface requirements is level and smooth without outstanding, to guarantee the normal mounting of equipment.For the thermal control after laying of assurance pipeline implements to be easy to the general assembly operation, and guarantee that the hydrazine storage tank can not be projected into outside the propulsion module, the upper surface of storage tank support 2 is 40mm apart from the axis height of engine bed 5, apart from satellite and the rocket interface 190mm.The pipe installation of this form is easy to operate, and it is larger especially to implement time space in thermal control, is convenient to the general assembly operation.
As shown in Figure 3, two pull bars 8 are housed on the storage tank support 2 are connected with upper flange 1, strengthen structural strength.The position of pull bar 8 can be adjusted in circumference according to the carrying situation when structure design.
According to the general carrier rocket of small satellite, external envelope size to propulsion module is restricted: housing 3 is 83.8 ° with the angle of inclination of satellite-rocket docking face (bottom surface of lower flange 4), propulsion module highly is 600mm between the end face of flange up and down, can adapt to the restriction that delivers the clean enveloping space with the satellite configuration that guarantees small satellite platform, installation space can also farthest be provided.With four intersection point places Y-axis and Z axis two slotted holes are arranged respectively housing 3, be used for pipeline by the 1N driving engine, in the YOZ plane with-the Z angular separation is that two director's circular holes are respectively left in the position on the upper side in 45 ° direction and the intersection of housing 3, is the crossing cabin hole of cable.This is that cable can not add switching, relates to the crossing cabin problem from the electronic compartment to the propulsion module owing to the requirement of equipment component owing to subsystem.In order after the docking of two cabins, still to open the plate operation, locate respectively to leave kidney-shaped cable penetrating hole, a place near the positions, 150mm place of upper flange 1 with each inclined to one side 45 ° at the intersection point of-Z axis on housing 3, the propulsion module inner cable passes with electronics below deck equipment or cable by this hole and is connected.The YOZ plane-Y-axis and-Z axis place quadrant and coordinate axle direction housing 3 at 45 ° increases porthole, the operation of convenient installation Piezoelectric switches with the junction of storage tank support 2.Cable operated mouth on the housing 3 and porthole can require and can do adaptive change under the prerequisite that does not interrupt propulsion module main structure housing stringer according to different satellites.
The installation form that the hydrazine fill valve that small satellite is general and the ion of gas fill valve and electric propulsion add the equipment such as valve has solidified, pipeline distance between center line storage tank support 2 upper surfaces (equipment attachment face) is optimal height apart from the 40mm empirical tests in the propulsion module, for guaranteeing pipeline height and fill valve and to add valve export pipeline height consistent, on housing 3, in the YOZ plane-Z axis partially+30 ° of directions of Y-axis and+Z axis partially+60 ° of directions of Y-axis respectively have a Φ 60 openings apart from the satellite and the rocket to interface 230mm place with the intersection of housing 3, add valve for the high-low pressure of installation electric propulsion system.On the housing 3, in the YOZ plane-Z axis partially+intersection of 45 ° of directions of Y-axis and housing 3 has a Φ 50 openings apart from the satellite and the rocket to interface 230mm place, is the mounting hole of hydrazine gas fill valve.On the housing 3, in the YOZ plane+Z axis partially-intersection of 45 ° of directions of Y-axis and housing 3 has a Φ 50 openings apart from the satellite and the rocket to interface 132mm place, is the mounting hole of hydrazine liquid fill valve.This opening mode is two propulsion system patterns, if single propulsion system, the opening that ion adds valve or hydrazine fill valve can be adjusted in 360 ° of scopes in the highly constant situation keeping.
The outside of housing 3 is evenly equipped with 8 struts 7, and an end of strut 7 is connected on the housing 3, and the other end is connected in the electronic compartment base plate and gets edge, plays a supporting role, and guarantees that electronic compartment is indeformable, and the position of strut 7 can be adjusted or cancels according to the electronic compartment size.
The content that is not described in detail in the specification sheets of the present invention belongs to those skilled in the art's known technology.
Claims (10)
1. General propelling module for small satellites is characterized in that comprising: upper flange (1), lower flange (4), storage tank support (2), engine bed and housing (3); Upper flange (1) and lower flange (4) lay respectively on two end faces of housing (3), and upper flange (1) is connected with electronic compartment, and lower flange (4) is the satellite-rocket docking face; Housing (3) is the truncated cone-shaped structure of hollow, and the inboard that storage tank support (2) is positioned at housing (3) is the position on the lower side; Storage tank support (2) is the lid-like that upper surface is smooth, lower surface is furnished with reinforced rib, the center of described lid-like has ion thruster pipeline outlet, storage tank support (2) propulsion module body coordinate system YOZ plane-Y-axis and-Z axis place quadrant and coordinate axle direction position at 45 ° has hydrazine bottle mounting hole; The upper surface of storage tank support (2) is the attachment face that equipment Pipe-Line is laid; Housing (3) with four intersection point places propulsion module body coordinate system Y-axis and Z axis an engine bed is housed respectively, wherein the support with two intersection point places of Y-axis is formal dress engine bed (5), with the support at two intersection point places of Z axis be angle mount engine bed (6), formal dress engine bed (5) is parallel with the Y-axis of propulsion module along the engine mounting face of Z-direction, and angle mount engine bed (6) becomes 15 ° of angles along the engine mounting face of Y direction with the Z axis of propulsion module; The origin of coordinates O of described propulsion module body coordinate system is at the theoretical center of described satellite-rocket docking face, X-axis is pointed to the direction of upper flange (1) along origin of coordinates O, Z axis crosses origin of coordinates O and perpendicular to X-axis, Z axis is directed towards ground under whole star state of flight, and Y-axis becomes right-handed system with Z axis, X-axis.
2. General propelling module for small satellites according to claim 1, it is characterized in that: the angle of the side of described truncated cone-shaped structure and satellite-rocket docking face is 83.8 °.
3. General propelling module for small satellites according to claim 2, it is characterized in that: pull bar (8) is housed on the described storage tank support (2), one end of pull bar (8) is connected with storage tank support (2), and the other end of pull bar (8) is connected with upper flange (1).
4. General propelling module for small satellites according to claim 2, it is characterized in that: the outside of described housing (3) is provided with strut (7), one end of strut (7) is connected on the housing (3), and the other end of strut (7) is connected on the base plate of electronic compartment.
5. General propelling module for small satellites according to claim 2 is characterized in that: on the described housing (3) respectively leave two engine pipelines perforation with four intersection point places propulsion module body coordinate system Y-axis and Z axis.
6. General propelling module for small satellites according to claim 2 is characterized in that: described housing (3) upper with-Z-direction angle be that 45 ° direction respectively leaves kidney-shaped cable penetrating hole, a place near the position at upper flange (1) 150mm place.
7. General propelling module for small satellites according to claim 2 is characterized in that: in the described propulsion module body coordinate system YOZ plane-Z axis partially+30 ° of directions of Y-axis and+Z axis partially+intersection of 60 ° of directions of Y-axis and housing (3) adds the valve mounting hole apart from what satellite and the rocket interface 230mm place had respectively an electric propulsion system.
8. General propelling module for small satellites according to claim 2 is characterized in that: in the described propulsion module body coordinate system YOZ plane-Z axis partially+intersection of 45 ° of directions of Y-axis and housing (3) has the mounting hole of hydrazine gas fill valve apart from satellite and the rocket interface 230mm place.
9. General propelling module for small satellites according to claim 2 is characterized in that: in the described propulsion module body coordinate system YOZ plane+Z axis partially-intersection of 45 ° of directions of Y-axis and housing (3) has the mounting hole of hydrazine liquid fill valve apart from satellite and the rocket interface 132mm place.
10. General propelling module for small satellites according to claim 2, it is characterized in that: the upper surface of described storage tank support (2) is 40mm apart from the axis height of engine bed (5), apart from satellite and the rocket interface 190mm.
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| CN 201110152846 CN102303710B (en) | 2011-06-08 | 2011-06-08 | General propelling module for small satellites |
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| CN 201110152846 CN102303710B (en) | 2011-06-08 | 2011-06-08 | General propelling module for small satellites |
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| CN102303710A CN102303710A (en) | 2012-01-04 |
| CN102303710B true CN102303710B (en) | 2013-05-01 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| FR3001714B1 (en) * | 2013-02-05 | 2016-08-26 | Astrium Sas | DEVICE FOR SUPPORTING AND MAINTAINING CRYOGENIC RESERVOIRS |
| CN104477415B (en) * | 2014-11-21 | 2017-01-11 | 上海卫星工程研究所 | Light-shading heat-insulation cover framework structure for spacecraft |
| CN106467176A (en) * | 2016-09-08 | 2017-03-01 | 上海卫星工程研究所 | The temp. control method in satellite booster cabin |
| CN106864773B (en) * | 2017-03-31 | 2018-05-22 | 北京蓝箭空间科技有限公司 | A kind of instrument cabin structure of vehicle |
| CN108298111B (en) * | 2017-12-26 | 2020-04-10 | 中国空间技术研究院 | Modular layout method for satellite chemical propulsion subsystem of public platform |
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| US6149104A (en) * | 1998-04-01 | 2000-11-21 | Trw Inc. | Structural layout for spacecraft including specialized compartment configuration |
| US6513760B1 (en) * | 1999-12-14 | 2003-02-04 | Kistler Aerospace Corporation | Logistics module system and method |
| CN101381003A (en) * | 2008-09-19 | 2009-03-11 | 航天东方红卫星有限公司 | Main load-carrying structure of spacecraft |
| CN202389602U (en) * | 2011-06-08 | 2012-08-22 | 航天东方红卫星有限公司 | Universal propelling module of small satellite |
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2011
- 2011-06-08 CN CN 201110152846 patent/CN102303710B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4880187A (en) * | 1986-01-16 | 1989-11-14 | Trw Inc. | Multipurpose modular spacecraft |
| US6149104A (en) * | 1998-04-01 | 2000-11-21 | Trw Inc. | Structural layout for spacecraft including specialized compartment configuration |
| US6513760B1 (en) * | 1999-12-14 | 2003-02-04 | Kistler Aerospace Corporation | Logistics module system and method |
| CN101381003A (en) * | 2008-09-19 | 2009-03-11 | 航天东方红卫星有限公司 | Main load-carrying structure of spacecraft |
| CN202389602U (en) * | 2011-06-08 | 2012-08-22 | 航天东方红卫星有限公司 | Universal propelling module of small satellite |
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