CN106347714A - Outboard radiator protective cover system with in-orbit popping and throwing functions - Google Patents
Outboard radiator protective cover system with in-orbit popping and throwing functions Download PDFInfo
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- CN106347714A CN106347714A CN201610795858.0A CN201610795858A CN106347714A CN 106347714 A CN106347714 A CN 106347714A CN 201610795858 A CN201610795858 A CN 201610795858A CN 106347714 A CN106347714 A CN 106347714A
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- protective cover
- cabin
- bullet
- blend stop
- orbit
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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
- B64G1/52—Protection, safety or emergency devices; Survival aids
-
- 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
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
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- Engineering & Computer Science (AREA)
- Health & Medical Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Wind Motors (AREA)
Abstract
The invention discloses an outboard radiator protective cover system with in-orbit popping and throwing functions, and belongs to the technical field of return satellites. The outboard radiator protective cover system comprises a protective cover, sealing silicone rubber, an unlocking device, middle supports, stop blocks and side silicone rubber. A barrier strip assembly of the protective cover abuts against a cabin body. The two stop blocks are fixed to the cabin body respectively and abut against end barrier strips of the protective cover. One end of the unlocking device is installed on the cabin body, and the other end of the unlocking device is installed at a foaming bullet of the protective cover body; one ends of the middle supports are fixed to the cabin body respectively, the other ends of the middle supports abut against the protective cover body, and silicone rubber pads are stuck to the contact faces of the middle supports and the protective cover body, wherein the two middle supports are located between the unlocking device and the two stop blocks. By adopting the scheme of multiple unilateral constraining of the sealing cabin and the protective cover, and reliable separation of the protective cover and the sealing cabin is achieved while it is ensured that powered phase loading rigidity and strength are borne.
Description
Technical field
The invention belongs to retrievable satellite technical field is and in particular to a kind of possess the irradiator out of my cabin that function thrown by in-orbit bullet
Protective cover system.
Background technology
Put into practice No. ten scientific experimentss satellites and be used exclusively for the research of " Microgravity Science and space life science " Space Experiments
Retrievable satellite.No trouserss during satellite launch, irradiator is arranged on outside Pressurized Module in Satellites, for avoiding satellite powered phase gas
Stream washes away the adverse effect with Aerodynamic Heating to irradiator, need to design irradiator protective cover, effectively to be protected to irradiator,
Entering the orbit rear defence guard shield need to be with celestial body safe separating.In space industry, a lot of spacecraft equipments are required for protective cover and are protected, such as
Remote sensing satellite, in order to protect camera, needs using camera protective cover；Some satellites are radiated load to reduce electromotor throat
Heat flow density near cylinder is it is also desirable to design protective cover is protected；Satellite thermal control air inlet setting protective cover is also had to enter
Row protection.But the universal area of these protective covers is less, and fillet mostly is circumferential clamped, and fillet is preferable.As practice
No. ten so designs are provided simultaneously with bearing powered phase overload and possess that function thrown by in-orbit bullet and area reaches 2m2Above irradiator
Protective cover still belongs to the first time at home.How to realize protective cover and separate reliability and powered phase rigidity and intensity system with nacelle
One is the problem needing to solve.
Content of the invention
In view of this, the invention provides a kind of possess the irradiator protective cover system out of my cabin that function thrown by in-orbit bullet, adopt
Protective cover and the scheme of the multiple Unilateral constraints of sealed compartment, structure is simple, easy for installation, and is ensureing to possess to bear powered phase load
It is achieved that the reliable separation of protective cover and sealed compartment under rigidity and intensity.
The present invention is achieved through the following technical solutions:
A kind of possess the irradiator protective cover system out of my cabin that function thrown by in-orbit bullet, comprising: protective cover, sealing silicone rubber, solution
Lock device, intermediate support, block and sidepiece silicone rubber；
Its ancillary equipment is the nacelle body of sealed compartment, and irradiator is arranged on nacelle, and this is internal；
Described protective cover includes shield body and blend stop assembly；
Wherein, described shield body is the arcuation sandwich being made up of inside panel, exterior skin and central layer, described central layer
Wrapped up cellular board and formed by two panels aluminium foil；It is filled with foaming bullet in the middle part of one end of shield body；
Described blend stop assembly includes oblique blend stop, terminal block bar and two side block bars；Two side block bars are separately fixed at protective cover
The both sides of body；Tiltedly blend stop and terminal block bar are separately fixed at the two ends of shield body, oblique blend stop, terminal block bar and two side block bars
The circulus of composition closing；Wherein, oblique blend stop is provided with one end of foaming bullet positioned at shield body；
Described unlocking device is used for connection and the unblock of protective cover and nacelle body；
The blend stop assembly of protective cover is conflicted on nacelle body；Two blocks are separately fixed on nacelle body, and conflict
On the terminal block bar of protective cover；One end of unlocking device is arranged on nacelle body, and the other end is arranged on the protective cover of protective cover originally
At the foaming bullet of body；One end of two intermediate supports is separately fixed on nacelle body, and the other end is conflicted anti-in protective cover
On guard shield body, and the contact surface in intermediate support and shield body is pasted with silicone rubber pad；Wherein, two intermediate supports divide
Wei Yu not be between unlocking device and two blocks.
Further, the generatrix direction of described shield body a size of 1900mm～2100mm, shield body corresponds to
Central angle be 52 °～62 °；The thickness of described inside panel and exterior skin is 0.4mm～0.6mm, and material is 2a12cz, institute
The thickness stating central layer is 9mm～11mm, and the material of central layer is lf2y0.04 × 4.
Further, two relative side center in shield body are respectively equipped with two built-in fittings, on built-in fitting
Parcel two-layer foaming adhesive tape.
Further, the foaming bullet diameters in described shield body are 70mm～80mm.
Further, the joint of described oblique blend stop, terminal block bar and two side block bars is coated respectively with silicone rubber.
Further, described oblique blend stop and the angle in the end face place face of shield body are more than 0 ° and are less than 90 °, terminal block
Bar is 0 ° with the angle in the end face place face of shield body.
Further, described block is wedge-shaped catch.
Further, the shield body surface of described protective cover and the gap of nacelle body surface are 35mm～45mm.
Further, the contact position of described oblique blend stop and terminal block bar and nacelle body is separately installed with sealing silicone rubber, and two
Individual side block bar is separately installed with sidepiece silicone rubber with the contact position of nacelle body.
Further, during finite element is built and touched, only set up constraint in the position of two blocks, and do not consider blend stop group
Part and the constraint of intermediate support.
Beneficial effect: any is connected due to only having unlocking device for the protective cover of (1) present invention and the connection of sealed compartment, other points
It is Unilateral constraints, separates good reliability, can achieve and efficiently separate, protective cover barycenter is not less than relative to the separating rate of celestial body
1m/s；After separating 10s, protective cover is not more than 10m with the nearest relative distance of sealed compartment, and separation process and separation rear defence guard shield are not
Interfere with equipment on sealed compartment and sealed compartment.
(2) present invention bears powered phase heat to the constraint of displacement it is ensured that protective cover possesses using multiple Unilateral constraints links
Load, the function of inertial load, irradiator protective cover can bear powered phase Aerodynamic Heating；
Brief description
Fig. 1 is the profile of the present invention
Fig. 2 is the top view of the present invention and the installation of nacelle body
Fig. 3 is finite element analyses simplified pinciple figure
Fig. 4 is the structure chart of shield body of the present invention
Wherein, 1- shield body, 2- blend stop assembly, 3- built-in fitting, 4- seals and props up in the middle of silicone rubber, 5- unlocking device, 6-
Seat, 7- nacelle body, 8- block, 9- sidepiece silicone rubber, 10- foaming bullet.
Specific embodiment
Develop simultaneously embodiment below in conjunction with the accompanying drawings, describes the present invention.
The invention provides a kind of possess the irradiator protective cover system out of my cabin that function thrown by in-orbit bullet, referring to attached Fig. 1 and 2,
Including: protective cover, sealing silicone rubber 4, unlocking device 5, intermediate support 6, block 8 and sidepiece silicone rubber 9；
Its ancillary equipment is the nacelle body 7 of sealed compartment, and irradiator is arranged in nacelle body 7；
Described protective cover includes shield body 1 and blend stop assembly 2.
Wherein, referring to accompanying drawing 3 and 4, described shield body 1 is to be pressed from both sides by the arcuation that inside panel, exterior skin and central layer form
Rotating fields, described central layer is located between inside panel and exterior skin；The generatrix direction of shield body 1 a size of 2000mm is corresponding
Central angle be 57 °；The thickness of arcuation sandwich is 11mm, and the thickness of inside and outside eyelid covering is 0.5mm, and material is
2a12cz, described central layer is wrapped up cellular board and formed by two panels aluminium foil, and the thickness of central layer is 10mm, and the material of central layer is
(lf2y represents aluminium foil model, 0.04 expression honeycomb plate thickness, and 4 represent the circumscribed circle of the honeycomb hole on cellular board for lf2y0.04 × 4
Diameter)；It is respectively equipped with two built-in fittings 3 in two relative side center of shield body 1, built-in fitting 3 wraps up two-layer
Foaming adhesive tape, during work, the pre-loading screw that built-in fitting 3 is provided with nacelle body 7 is inconsistent；In one end of shield body 1
Portion is filled with the foaming bullet 10 of a diameter of 75mm.
Described blend stop assembly 2 includes oblique blend stop, terminal block bar and two side block bars；Two side block bars are separately fixed at protective cover
The both sides of body 1；Tiltedly blend stop and terminal block bar are separately fixed at the two ends of shield body 1, oblique blend stop, terminal block bar and two side blocks
The circulus of bar composition closing, the joint of oblique blend stop, terminal block bar and two side block bars is coated respectively with the silicon rubber for sealing
Glue, prevents Orbital heat flux from washing away；Wherein, oblique blend stop is provided with one end of foaming bullet 10 positioned at shield body 1, oblique blend stop with anti-
The angle in the end face place face of guard shield body 1 is more than 0 ° and is less than 90 °, the end face place face of terminal block bar and shield body 1
Angle is 0 °；Blend stop assembly 2 and shield body 1 are surrounded and are formed the box-like protective cover only having one end open, for installing heat
Control product.
Described block 8 is wedge-shaped catch.
Described unlocking device 5 is used for, during portion's dress and general assembly, protective cover being fixed on nacelle body 7, in nacelle
After body 7 is entered the orbit, unlocking device 5 ignition operation, provide momentum it is ensured that the reliable separation of protective cover and nacelle body 7 for protective cover,
Realize the throwing lid action of protective cover.
Integrated connection relation is as follows: the blend stop assembly 2 of protective cover is conflicted on nacelle body 7, and the protective cover of protective cover is originally
Body 1 surface is 40mm with the gap on nacelle body 7 surface；Wherein, the contact position difference of oblique blend stop and terminal block bar and nacelle body 7
Sealing silicone rubber 4 is installed, the contact position of two side block bars and nacelle body 7 is separately installed with sidepiece silicone rubber 9, described sealing
Silicone rubber 4 and sidepiece silicone rubber 9 are used for preventing Orbital heat flux from irradiator is washed away, and simultaneously work as position-limiting action；
The big end of two blocks 8 is separately fixed on nacelle body 7, and the small end of two blocks 8 is conflicted at the end of protective cover
On blend stop, for the clamping of protective cover and spacing；One end of unlocking device 5 is arranged on nacelle body 7, and the other end is arranged on anti-
At the foaming bullet 10 of the shield body 1 of guard shield, realize connection and the unblock of protective cover and nacelle body 7；Two centres are propped up
One end of seat 6 is separately fixed on nacelle body 7, and the other end is conflicted in the shield body 1 of protective cover, and in intermediate support
6 are pasted with silicone rubber pad with the contact surface of shield body 1, for providing cross-brace to protective cover, and limit nacelle body 7
Displacement；Wherein, two intermediate supports 6 are located between unlocking device 5 and two blocks 8 respectively.
Operation principle: protective cover is connected on nacelle body 7 by unlocking device 5, protective cover lower end is with nacelle body 7
Two blocks 8 are spacing, and the protective cover back side is supported with two intermediate supports 6, and therefore, protective cover and nacelle body 7 have at 5 points and connect
Touch, wherein, be fixed constraint at unlocking device 5, remaining 4 points is spacing constraint, as Unilateral constraints；
In existing finite element method, Frequency Response Analysis can not be carried out to non-linear Unilateral constraints；Therefore, originally
Invention has carried out rational simplification during finite element is built and touched；According to the vibration state in vibration test for the protective cover: when anti-
When guard shield vibrates swing inwards, blend stop assembly 2 stress of protective cover, rigidity is preferable；When protective cover swings out, two blocks
8 position stress；Therefore, FEM (finite element) model is set up and is only set up constraint in the position of two blocks 8, and does not consider blend stop assembly 2
And the constraint of intermediate support 6；I.e. whole star coordinate system (length direction of whole star is the longitudinal axis, and the direction with axis oriented normal is transverse axis)
Lower constraint and the displacement in axis oriented normal direction, do not consider the length travel under whole star coordinate system and corner；Experiment proves that, three
The each several part acceleration responsive result of calculation of individual direction incentive action low protection cover all overlaps well with whole-satellite experiment result, this kind of
Modeling pattern can be used as the sign of finite element modeling.
During work, unlocking device 5 igniting after, to thrust from protective cover to the direction away from nacelle body 7, protective cover lower end
Rotate around two blocks 8, simultaneously to the direction translational away from nacelle body 7, realize protective cover bullet throw, and with nacelle body 7
Separate.
In sum, these are only presently preferred embodiments of the present invention, be not intended to limit protection scope of the present invention.
All any modification, equivalent substitution and improvement within the spirit and principles in the present invention, made etc., should be included in the present invention's
Within protection domain.
Claims (10)
1. a kind of protective cover system of irradiator out of my cabin possessing in-orbit bullet throwing function is it is characterised in that include: protective cover, sealing
Silicone rubber (4), unlocking device (5), intermediate support (6), block (8) and sidepiece silicone rubber (9)；
Its ancillary equipment is the nacelle body (7) of sealed compartment, and irradiator is arranged in nacelle body (7)；
Described protective cover includes shield body (1) and blend stop assembly (2)；
Wherein, described shield body (1) is the arcuation sandwich being made up of inside panel, exterior skin and central layer, described central layer
Wrapped up cellular board and formed by two panels aluminium foil；It is filled with foaming bullet (10) in the middle part of one end of shield body (1)；
Described blend stop assembly (2) includes oblique blend stop, terminal block bar and two side block bars；Two side block bars are separately fixed at protective cover originally
The both sides of body (1)；Tiltedly blend stop and terminal block bar are separately fixed at the two ends of shield body (1), oblique blend stop, terminal block bar and two sides
The circulus of blend stop composition closing；Wherein, oblique blend stop is provided with one end of foaming bullet (10) positioned at shield body (1)；
Described unlocking device (5) is used for connection and the unblock of protective cover and nacelle body (7)；
The blend stop assembly (2) of protective cover is conflicted on nacelle body (7)；Two blocks (8) are separately fixed at nacelle body (7)
On, and conflict on the terminal block bar of protective cover；One end of unlocking device (5) is arranged on nacelle body (7), and the other end is arranged on anti-
Foaming bullet (1) (0) place of the shield body (1) of guard shield；One end of two intermediate supports (6) is separately fixed at nacelle body
(7) on, the other end is conflicted in the shield body (1) of protective cover, and connecing in intermediate support (6) and shield body (1)
Contacting surface is pasted with silicone rubber pad；Wherein, two intermediate supports (6) are located between unlocking device (5) and two blocks (8) respectively.
2. as claimed in claim 1 a kind of possess in-orbit bullet throw function the protective cover system of irradiator out of my cabin it is characterised in that
The generatrix direction a size of 1900mm～2100mm of described shield body (1), the corresponding central angle of shield body (1) is
52 °～62 °；The thickness of described inside panel and exterior skin is 0.4mm～0.6mm, and material is 2a12cz, the thickness of described central layer
Spend for 9mm～11mm, the material of central layer is lf2y0.04 × 4.
3. as claimed in claim 1 a kind of possess in-orbit bullet throw function the protective cover system of irradiator out of my cabin it is characterised in that
It is respectively equipped with two built-in fittings (3) in two relative side center of shield body (1), built-in fitting (3) is upper to wrap up two-layer
Foaming adhesive tape.
4. as claimed in claim 1 a kind of possess in-orbit bullet throw function the protective cover system of irradiator out of my cabin it is characterised in that
A diameter of 70mm～the 80mm of foaming bullet (10) on described shield body (1).
5. as claimed in claim 1 a kind of possess in-orbit bullet throw function the protective cover system of irradiator out of my cabin it is characterised in that
The joint of described oblique blend stop, terminal block bar and two side block bars is coated respectively with silicone rubber.
6. as claimed in claim 1 a kind of possess in-orbit bullet throw function the protective cover system of irradiator out of my cabin it is characterised in that
The angle in the end face place face of described oblique blend stop and shield body (1) is more than 0 ° and less than 90 °, terminal block bar and shield body
(1) angle in end face place face is 0 °.
7. as claimed in claim 1 a kind of possess in-orbit bullet throw function the protective cover system of irradiator out of my cabin it is characterised in that
Described block (8) is wedge-shaped catch.
8. as claimed in claim 1 a kind of possess in-orbit bullet throw function the protective cover system of irradiator out of my cabin it is characterised in that
Shield body (1) surface of described protective cover and the gap on nacelle body (7) surface are 35mm～45mm.
9. as claimed in claim 1 a kind of possess in-orbit bullet throw function the protective cover system of irradiator out of my cabin it is characterised in that
Described oblique blend stop and terminal block bar are separately installed with sealing silicone rubber (4), two side block bars and cabin with the contact position of nacelle body (7)
The contact position of body body (7) is separately installed with sidepiece silicone rubber (9).
10. a kind of as claimed in claim 1 possess the irradiator protective cover system out of my cabin that function thrown by in-orbit bullet, and its feature exists
In, during finite element is built and touched, only in the position of two blocks (8), foundation constrains, and does not consider blend stop assembly (2) and centre
The constraint of bearing (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610795858.0A CN106347714B (en) | 2016-08-31 | 2016-08-31 | A kind of radiator protective cover system out of my cabin for having in-orbit bullet and throwing function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610795858.0A CN106347714B (en) | 2016-08-31 | 2016-08-31 | A kind of radiator protective cover system out of my cabin for having in-orbit bullet and throwing function |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106347714A true CN106347714A (en) | 2017-01-25 |
| CN106347714B CN106347714B (en) | 2018-06-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610795858.0A Active CN106347714B (en) | 2016-08-31 | 2016-08-31 | A kind of radiator protective cover system out of my cabin for having in-orbit bullet and throwing function |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110789745A (en) * | 2019-10-25 | 2020-02-14 | 西安航天动力试验技术研究所 | A compress tightly release mechanism for spacecraft is prevented insulating against heat and separation test |
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|---|---|---|---|---|
| US5823477A (en) * | 1995-12-22 | 1998-10-20 | Hughes Electronics Corporation | Device and method for minimizing radiator area required for heat dissipation on a spacecraft |
| CN1610628A (en) * | 2002-01-02 | 2005-04-27 | 易兹埃斯特里姆联合股份公司 | Space craft with extensible radiators |
| DE10340092A1 (en) * | 2003-08-30 | 2005-05-04 | Ohb Orbitale Hochtechnologie B | Radiator with sandwich structure for use in satellites, includes integral loop heat pipe comprising flanged aluminum profiles |
| CN102673803A (en) * | 2011-03-17 | 2012-09-19 | 塔莱斯公司 | Structural satellite panel with integrated heat exchangers |
| CN102941926A (en) * | 2012-11-06 | 2013-02-27 | 北京空间飞行器总体设计部 | Space debris prevention type heat radiator |
-
2016
- 2016-08-31 CN CN201610795858.0A patent/CN106347714B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5823477A (en) * | 1995-12-22 | 1998-10-20 | Hughes Electronics Corporation | Device and method for minimizing radiator area required for heat dissipation on a spacecraft |
| CN1610628A (en) * | 2002-01-02 | 2005-04-27 | 易兹埃斯特里姆联合股份公司 | Space craft with extensible radiators |
| DE10340092A1 (en) * | 2003-08-30 | 2005-05-04 | Ohb Orbitale Hochtechnologie B | Radiator with sandwich structure for use in satellites, includes integral loop heat pipe comprising flanged aluminum profiles |
| CN102673803A (en) * | 2011-03-17 | 2012-09-19 | 塔莱斯公司 | Structural satellite panel with integrated heat exchangers |
| CN102941926A (en) * | 2012-11-06 | 2013-02-27 | 北京空间飞行器总体设计部 | Space debris prevention type heat radiator |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110789745A (en) * | 2019-10-25 | 2020-02-14 | 西安航天动力试验技术研究所 | A compress tightly release mechanism for spacecraft is prevented insulating against heat and separation test |
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| Publication number | Publication date |
|---|---|
| CN106347714B (en) | 2018-06-12 |
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