CN102303710A - General propelling module for small satellites - Google Patents
General propelling module for small satellites Download PDFInfo
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- CN102303710A CN102303710A CN201110152846A CN201110152846A CN102303710A CN 102303710 A CN102303710 A CN 102303710A CN 201110152846 A CN201110152846 A CN 201110152846A CN 201110152846 A CN201110152846 A CN 201110152846A CN 102303710 A CN102303710 A CN 102303710A
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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 small satellite application and development, the small satellite function is constantly strengthened, and system also becomes increasingly complex.In order to satisfy the needs of long-term attitude in orbit of small satellite and track control, small satellite need carry more fuel and perhaps adopt the rail control engine of electric propulsion as small satellite.Simultaneously, along with the shortening of small satellite lead time, also need the part development of satellite can walk abreast and carry out, to optimize the development flow process, the quickening Development Schedule with experimental work.
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 influence 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 bigger to influence meeting when making the electricity consumption thruster.In addition, because propulsion system and other electronic machine are installed in the same cabin, 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 deficiency of prior art, a kind of general propulsion module of small satellite that holds two propulsion systems is provided, can reduce the complexity of satellite layout and general assembly operation simultaneously so that small satellite carries more fuel.
Technical solution of the present invention is: the general propulsion module of small satellite 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 said lid-like has ion thruster pipeline outlet, the storage tank support propulsion module body coordinate system YOZ plane-Y-axis belongs to quadrant and becomes 45 ° direction position to have hydrazine bottle mounting hole with coordinate axle with-Z axle; The upper surface of storage tank support is the attachment face of equipment and pipe installation; Housing an engine bed respectively is housed with four intersection point places propulsion module body coordinate system Y-axis and Z axle; 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 axle 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 axle of propulsion module; The origin of coordinates O of described propulsion module body coordinate system is at the theoretical center of said satellite-rocket docking face; X-axis is pointed to the direction of upper flange along origin of coordinates O; The Z axle crosses origin of coordinates O and perpendicular to X-axis, the Z axle is directed towards ground under whole star state of flight, and Y-axis becomes right-handed system with Z axle, 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 axle respectively leave two engine pipelines perforation.On the described housing with-Z-direction angle be that 45 ° direction respectively leaves waist shape cable penetrating hole, a place near the position at upper flange 150mm place.In the described propulsion module body coordinate system YOZ plane-the Z axle partially+30 ° of directions of Y-axis and+the Z axle 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 electric propulsion system respectively.In the described propulsion module body coordinate system YOZ plane-the Z axle 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+the Z axle 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-rocket docking face 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 of the influence of driving engine plume, make electric thruster become possibility as the rail control engine of small satellite to sensor on the star;
(2) adopt independent propulsion module form can at utmost increase the distance of sensor on driving engine and the star; Reduce the plume influence; Electronic compartment and propulsion module carry out as two main lines simultaneously simultaneously; Propulsion module can independently carry out 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 the 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 made up of propulsion module main body and storage tank support 2 two parts, and wherein the propulsion module main body is divided into upper flange 1, lower flange 4, housing 3 three parts again.In order to narrate conveniently, the body coordinate system (O-XYZ) that at first defines propulsion module 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 axle: 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.
Like Fig. 1, shown in Figure 2, propulsion module docks with the satellite electron cabin through 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 two pin holes on the upper flange 1 in addition, 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 butt joint 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 is formed.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-have gap, the operational observations mouth when this gap is the Piezoelectric switches crossing cabin in Y-axis and the-Z axle place quadrant.Storage tank support 2 the YOZ plane-Y-axis becomes 45 ° direction to have through hole with-Z axle place quadrant with coordinate axle, this through hole is a 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; When if hydrazine advances independent installation; 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 on storage tank support 2, cancel or adjust the equipment mounting hole according to the equipment situation.The upper surface of storage tank support 2 is attachment faces of major equipment and pipe installation, and the level and smooth nothing of surface requirements is 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-rocket docking face 190mm.The pipe installation of this form is easy to operate, and it is bigger 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 and are connected additional strengthening intensity with upper flange 1.The position of pull bar 8 can be adjusted in circumference according to the carrying situation when structure design.
According to small satellite general-duty carrier rocket; External envelope size to propulsion module has restriction: 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; To guarantee that small satellite flat-bed satellite configuration can adapt to the restriction that delivers the clean enveloping space, can also farthest provide installation space.With four intersection point places Y-axis and Z axle two slotted holes are arranged respectively housing 3; Be used for pipeline through 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 ° the 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 butt joint of two cabins, still to open the plate operation; On housing 3, locate for each inclined to one side 45 ° respectively to leave waist shape cable penetrating hole, a place near the positions, 150mm place of upper flange 1 with the intersection point of-Z axle, the propulsion module inner cable passes with electronics below deck equipment or cable through this hole and is connected.The YOZ plane-Y-axis and-Z axle place quadrant become the junction of 45 ° direction housing 3 and storage tank support 2 to increase porthole, the operation of convenient installation Piezoelectric switches with coordinate axle.Cable operated mouth on the housing 3 and porthole can require and can under the prerequisite that does not interrupt propulsion module main structure housing stringer, do adaptive change according to different satellites.
The installation form that the ion of small satellite general-duty hydrazine fill valve and gas fill valve and electric propulsion adds 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; Consistent for guaranteeing pipeline height and fill valve and adding valve export pipeline height; On housing 3; In the YOZ plane-the Z axle partially+30 ° of directions of Y-axis and+the Z axle partially+intersection of 60 ° of directions of Y-axis and housing 3 has a Φ 60 openings apart from the satellite and the rocket respectively to interface 230mm place, the high-low pressure that is used to install electric propulsion system adds valve.On the housing 3, in the YOZ plane-the Z axle 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+the Z axle 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, ion adds the opening of valve or hydrazine fill valve and under maintenance height unmodified situation, can in 360 ° of scopes, adjust.
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.
Housing 3 a 1N engine bed respectively is housed with four intersection point places Y-axis and Z axle; Wherein the support with two intersection point places of Y-axis is a formal dress 1N engine bed 5; With the support at two intersection point places of Z axle be angle mount 1N engine bed 6; Formal dress 1N engine bed 5 is parallel with the Y-axis of propulsion module along the engine mounting face of Z-direction, and angle mount 1N engine bed 6 becomes 15 ° of angles with the Z axle of propulsion module respectively along the engine mounting face of Y direction.Four engine bed bottom surfaces are all parallel with satellite-rocket docking face (bottom surface of lower flange 4), and the 1N engine installation axially bored line of vertical direction is vertical with the satellite-rocket docking face.From being 230mm, this 1N engine export pipeline height that highly can guarantee horizontal direction is 40mm to the 1N engine installation axially bored line of horizontal direction, the bending situation can not occur apart from the satellite-rocket docking identity distance.It is 181mm that the vertical direction engine mounting face leaves apart from the satellite-rocket docking identity distance.
The content of not doing to describe in detail in the specification sheets of the present invention belongs to those skilled in the art's known technology.
Claims (10)
1. the general propulsion module of small satellite 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 said lid-like has ion thruster pipeline outlet, storage tank support (2) propulsion module body coordinate system YOZ plane-Y-axis belongs to quadrant and becomes 45 ° direction position to have hydrazine bottle mounting hole with coordinate axle with-Z axle; The upper surface of storage tank support (2) is the attachment face of equipment and pipe installation; Housing (3) an engine bed respectively is housed with four intersection point places propulsion module body coordinate system Y-axis and Z axle; 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 axle 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 axle of propulsion module; The origin of coordinates O of described propulsion module body coordinate system is at the theoretical center of said satellite-rocket docking face; X-axis is pointed to the direction of upper flange (1) along origin of coordinates O; The Z axle crosses origin of coordinates O and perpendicular to X-axis, the Z axle is directed towards ground under whole star state of flight, and Y-axis becomes right-handed system with Z axle, Y-axis.
2. the general propulsion module of small satellite according to claim 1 is characterized in that: the angle of the side of described truncated cone-shaped structure and satellite-rocket docking face is 83.8 °.
3. the general propulsion module of small satellite according to claim 2 is characterized in that: pull bar (8) is housed on the described storage tank support (2), and an 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. the general propulsion module of small satellite according to claim 2 is characterized in that: the outside of described housing (3) is provided with strut (7), and an 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. the general propulsion module of small satellite according to claim 2 is characterized in that: on the described housing (3) and four intersection point places propulsion module body coordinate system Y-axis and Z axle respectively leave two engine pipelines perforation.
6. the general propulsion module of small satellite according to claim 2 is characterized in that: described housing (3) go up with-Z-direction angle be that 45 ° direction respectively leaves waist shape cable penetrating hole, a place near the position at upper flange (1) 150mm place.
7. the general propulsion module of small satellite according to claim 2 is characterized in that: in the described propulsion module body coordinate system YOZ plane-the Z axle partially+30 ° of directions of Y-axis and+the Z axle partially+intersection of 60 ° of directions of Y-axis and housing (3) adds the valve mounting hole apart from the satellite and the rocket to what 230mm place in interface had electric propulsion system respectively.
8. the general propulsion module of small satellite according to claim 2 is characterized in that: in the described propulsion module body coordinate system YOZ plane-the Z axle partially+intersection of 45 ° of directions of Y-axis and housing (3) has the mounting hole of hydrazine gas fill valve to interface 230mm place apart from the satellite and the rocket.
9. the general propulsion module of small satellite according to claim 2 is characterized in that: in the described propulsion module body coordinate system YOZ plane+the Z axle partially-intersection of 45 ° of directions of Y-axis and housing (3) has the mounting hole of hydrazine liquid fill valve to interface 132mm place apart from the satellite and the rocket.
10. the general propulsion module of small satellite according to claim 2 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-rocket docking face 190mm.
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| Application Number | Priority Date | Filing Date | Title |
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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 true CN102303710A (en) | 2012-01-04 |
| CN102303710B CN102303710B (en) | 2013-05-01 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104477415A (en) * | 2014-11-21 | 2015-04-01 | 上海卫星工程研究所 | Light-shading heat-insulation cover framework structure for spacecraft |
| CN104968566A (en) * | 2013-02-05 | 2015-10-07 | 空中客车防务和空间公司 | Device for retaining a tank in an aircraft |
| 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 |
| CN106864773A (en) * | 2017-03-31 | 2017-06-20 | 陕西蓝箭航天技术有限公司 | A kind of instrument cabin structure of vehicle |
| CN108298111A (en) * | 2017-12-26 | 2018-07-20 | 中国空间技术研究院 | A kind of common platform satellite chemical propulsion subsystem modular layout method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104968566A (en) * | 2013-02-05 | 2015-10-07 | 空中客车防务和空间公司 | Device for retaining a tank in an aircraft |
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| CN108298111A (en) * | 2017-12-26 | 2018-07-20 | 中国空间技术研究院 | A kind of common platform satellite chemical propulsion subsystem modular layout method |
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| CN102303710B (en) | 2013-05-01 |
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