CN106945850A - Satellite load packaging type prestress thin wall taper gravity gradient boom - Google Patents
Satellite load packaging type prestress thin wall taper gravity gradient boom Download PDFInfo
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- CN106945850A CN106945850A CN201710052604.4A CN201710052604A CN106945850A CN 106945850 A CN106945850 A CN 106945850A CN 201710052604 A CN201710052604 A CN 201710052604A CN 106945850 A CN106945850 A CN 106945850A
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- China
- Prior art keywords
- bar
- thin walled
- load
- satellite
- small end
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Classifications
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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
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/34—Guiding or controlling apparatus, e.g. for attitude control using gravity gradient
Abstract
Invention provides a kind of satellite load packaging type prestress thin wall taper gravity gradient boom, it is characterised in that applied to spacecraft field, including satellite, thin walled bar, load and small end frame.The small end frame includes baffle plate I, baffle plate II and rotating shaft.The thin walled bar is integrally conical, and one end that the thin walled bar is relatively large in diameter is big end, and the less one end of diameter is small end.The load is installed on small end frame.The big end of the thin walled bar is fixed on the side of satellite by flange, and the small end of the thin walled bar is fixed in load through speed limit slot.The solution have the advantages that unquestionable, the present invention is simple in construction, and without unwanted motion pair, the big end of bar is fixed on satellite and can kept relative stability, and can effectively resist external resistance.The gravity gradient boom without additional drive device to just completing voluntarily to stretch after space.Thin walled bar can realize flattening, it is achieved thereby that high magnification.
Description
Technical field
The present invention relates to space extension means technical field, and in particular to a kind of satellite load packaging type prestress thin wall cone
Shape gravity gradient boom.
Background technology
Space satellite around the earth orbit when, the earth's core has different gravitation to satellite various pieces quality, gravitation and
The referred to as gravity of making a concerted effort of centrifugal force.Satellite simply can be divided into the matter of the liftoff heart nearer quality m1 and the liftoff heart farther out
Measure m2, because the liftoff hearts of m1 are nearer, the gravitation being subject to is more than centrifugal force, and gravity points to the earth's core, m2 the is liftoff heart farther out, so
The gravitation being subject to is less than centrifugal force, gravity dorsad the earth's core.Satellite midpoint O gravity is zero.So as to form a recovery around O points
Torque, i.e. gravity gradient torque.
Gravity gradient torque is used for attitude of the stabilized satellite in space motion, and the size of its torque is removed and orbit altitude and shape
Shape has outside the Pass, also and each axle rotary inertia of satellite difference it is relevant.Each axle rotary inertia difference is bigger, and attitude stabilization is better.And weigh
Power gradient bar is played a key effect to regulation rotary inertia, and gravity gradient boom is stretched out after satellier injection, can rotate each axle of satellite
The difference of inertia reaches tens times even more than hundred times.The final axes of least inertia for causing satellite is stable in local plumb line direction,
The stable normal direction in orbit plane of axes of most inertia.This state is exactly the statokinetic of the stabilization of satellite.
With the development of space technology, space structure is maximized, complicated increasingly, but spacecraft mass carried and effectively
The storage area of load is limited, and the quality of rigid gravity gradient boom, size will be very restricted.Gravity gradient boom
Bar length is stored for general satellite the problem of be one very big, and the gravity gradient boom of various countries' design is under this basic premise
Design.And gravity gradient boom now is pursued be then it is more light and handy, it is simple in construction, occupy little space.In design weight ladder
High reliability, high magnification, lightweight, low power consumption of its expansion etc. are required during degree bar.Traditional rigid gravity gradient boom exists
Shortcomings are exposed under space technology and space environment now.
The content of the invention
It is an object of the invention to provide a kind of load packaging type prestress thin wall taper gravity gradient boom, the load packaging type
Prestress thin wall taper gravity gradient boom have the advantages that high magnification, self-deploy, it is lightweight, high rigidity, highly reliable, be suitable for
Satellite in orbit adjusts its attitude.The storage area for solving payload is limited, the problem of gravity gradient boom is not easily contained.
To realize that the technical scheme that the object of the invention is used is such, satellite load packaging type prestress thin wall taper
Gravity gradient boom, it is characterised in that applied to spacecraft field, including satellite, thin walled bar, load and small end frame.
The small end frame includes baffle plate I, baffle plate II and rotating shaft, and the baffle plate I and baffle plate II are arranged symmetrically, the baffle plate
Rotating shaft is installed between I and baffle plate II.The baffle plate I and baffle plate II are fixed together by cross bar, and the one of the cross bar
End is fixed on baffle plate I, and the other end is fixed on baffle plate II.Speed limit slot is provided with the cross bar.
The thin walled bar is integrally conical, and one end that the thin walled bar is relatively large in diameter is big end, and the less one end of diameter is
Small end, what the thin walled bar small end to a diameter of between big end was seamlessly transitted.The thin walled bar can be crimped along its length
After restore to the original state.
The load is installed on small end frame by rotating shaft, and the load is located between baffle plate I and baffle plate II.It is described to carry
Lotus can rotate around the shaft.
The big end of the thin walled bar is fixed on satellite by flange, and the small end of the thin walled bar is fixed through speed limit slot
In in load.
The satellite enter planned orbit before, thin walled bar is contraction state, the thin walled bar by small end with load around
Rotating shaft rotates and coats load, and now thin walled bar is rolled into flat, until the adjacent satellite of small end frame so that thin walled bar
It can not further shrink, then fix load by locking mechanism so that load can not rotate, thin walled bar can not also stretch.
After satellite enters planned orbit, the locking mechanism on small end frame is opened so that load can rotate, now thin walled bar
Extended configuration is changed into from crimp shrinkage state.Thin walled bar is slowly deployed automatically by prestressing force, and due to small end frame upper limit speed
The effect of slot so that the speed of thin walled bar expansion process keeps moderate.After being fully deployed, satellite and small end frame and it is installed on
The distance between load on small end frame reaches maximum, and last satellite enters normal work stage.
Further, the thin-walled bar side wall has fin at two of the axisymmetrical on thin walled bar.The fin with it is thin
The intersection of wall bar is rounding off.
The solution have the advantages that unquestionable, the present invention is simple in construction, and without unwanted motion pair, the big end of bar is consolidated
Being scheduled on satellite to keep relative stability, and can effectively resist external resistance, such as space debris, radiation.The gravity gradient
Bar without the power such as electric power, chemical energy, pneumatic and drive device to just completing voluntarily to stretch after space.Thin walled bar can be real
Existing flattening, it is achieved thereby that high magnification.Thin walled bar uses thin-wall conical structure, its quality is significantly less than the matter of cylindrical bar
Amount, and because without power source and related driving device, total quality mitigates.
Brief description of the drawings
Fig. 1 is contraction state schematic diagram of the invention；
Fig. 2 is extended configuration schematic diagram of the invention；
Fig. 3 is small end block schematic illustration；
Fig. 4 is thin walled bar schematic cross-section；.
In figure：Satellite 1, thin walled bar 2, load 3, small end frame 4, rotating shaft 401, speed limit slot 402, flange 5.
Embodiment
With reference to embodiment, the invention will be further described, but should not be construed above-mentioned subject area of the invention only
It is limited to following embodiments.Without departing from the idea case in the present invention described above, according to ordinary skill knowledge and used
With means, various replacements and change are made, all should be included within the scope of the present invention.
Satellite load packaging type prestress thin wall taper gravity gradient boom, it is characterised in that applied to spacecraft field, bag
Include satellite 1, thin walled bar 2, load 3 and small end frame 4.
The small end frame 4 includes baffle plate I 403, baffle plate II 404 and rotating shaft 401, the baffle plate I 403 and baffle plate II 404
It is arranged symmetrically, rotating shaft 401 is installed between the baffle plate I 403 and baffle plate II 404.The baffle plate I 403 and baffle plate II 404 pass through
Cross bar is fixed together, and one end of the cross bar is fixed on baffle plate I 403, and the other end is fixed on baffle plate II 404.Institute
State and be provided with cross bar speed limit slot 402.
The thin walled bar 2 is integrally conical, and one end that the thin walled bar 2 is relatively large in diameter is big end, the less one end of diameter
For small end, what the small end of thin walled bar 2 to a diameter of between big end was seamlessly transitted.The thin walled bar 2 can be along its length
Restored to the original state after curling.
The load 3 is installed on small end frame 4 by rotating shaft 401, and the load 3 is located at baffle plate I 403 and baffle plate II
Between 404.The load 3 can be with around the shaft 401 rotations.
The big end of the thin walled bar 2 is fixed on satellite 1 by flange 5, and the small end of the thin walled bar 2 passes through speed limit slot
402 are fixed in load 3.
The satellite 1 enters before planned orbit, and thin walled bar 2 is contraction state, and the thin walled bar 2 is by small end with load
3 401 rotations around the shaft and load 3 is coated, now thin walled bar 2 is rolled into flat, until the adjacent satellite 1 of small end frame 4,
So that thin walled bar 2 can not further shrink, then load 3 is fixed by locking mechanism so that load 3 can not rotate, thin-walled
Bar 2 can not also stretch.After satellite 1 enters planned orbit, the locking mechanism on small end frame 4 is opened so that the energy of load 3
Enough rotations, now thin walled bar 2 is changed into extended configuration from crimp shrinkage state.Thin walled bar 2 is slowly deployed automatically by prestressing force, again
Due to the effect of speed limit slot 402 on small end frame 4 so that the speed of the expansion process of thin walled bar 2 keeps moderate.It is fully deployed
Afterwards, satellite 1 reaches maximum with the distance between small end frame 4 and the load 3 being installed on small end frame 4, and last satellite 1 enters
Normal work stage.
Horizontal plane where the rotating shaft 401 is higher than the horizontal plane where speed limit slot 402.
The side wall of thin walled bar 2 has fin 201 at two of the axisymmetrical on thin walled bar 2.The fin 201 with it is thin
The intersection of wall bar 2 is rounding off.
Claims (2)
1. satellite load packaging type prestress thin wall taper gravity gradient boom, it is characterised in that applied to spacecraft field, including
Satellite (1), thin walled bar (2), load (3) and small end frame (4)；
The small end frame (4) includes baffle plate I (403), baffle plate II (404) and rotating shaft (401), the baffle plate I (403) and baffle plate
II (404) are arranged symmetrically, and rotating shaft (401) is provided between the baffle plate I (403) and baffle plate II (404)；The baffle plate I (403)
It is fixed together with baffle plate II (404) by cross bar, one end of the cross bar is fixed on baffle plate I (403), and the other end is solid
Due on baffle plate II (404)；The speed limit slot (402) is provided with the cross bar；
The thin walled bar (2) is integrally conical, and one end that the thin walled bar (2) is relatively large in diameter is big end, the less one end of diameter
For small end, what thin walled bar (2) small end to a diameter of between big end was seamlessly transitted；The thin walled bar (2) can be along length
Restored to the original state after the curling of direction；
The load (3) is installed on small end frame (4) by rotating shaft (401), and the load (3) is located at baffle plate I (403) and gear
Between plate II (404)；The load (3) (401) can rotate around the shaft；
The big end of the thin walled bar (2) is fixed on satellite (1) by flange (5), and the small end of the thin walled bar (2) passes through speed limit
Slot (402) is fixed in load (3)；
The satellite (1) enters before planned orbit, and thin walled bar (2) is contraction state, and the thin walled bar (2) is by small end with load
(401) rotate and coat load (3) lotus (3) around the shaft, and now thin walled bar (2) is rolled into flat, until small end frame
(4) adjacent satellite (1) so that thin walled bar (2) can not further shrink, and then fix load (3) by locking mechanism so that
Load (3) can not rotate, and thin walled bar (2) can not also stretch；After satellite (1) enters planned orbit, by small end frame (4)
Locking mechanism open so that load (3) can rotate, and now thin walled bar (2) is changed into extended configuration from crimp shrinkage state.It is thin
Wall bar (2) is slowly deployed automatically by prestressing force, and due to the effect of speed limit slot (402) on small end frame (4) so that thin-walled
The speed of bar (2) expansion process keeps moderate.After being fully deployed, satellite (1) and small end frame (4) and small end frame is installed on
(4) the distance between load (3) on reaches maximum, and last satellite (1) enters normal work stage.
2. satellite load packaging type prestress thin wall taper gravity gradient boom according to claim 1, it is characterised in that institute
State thin walled bar (2) side wall have on thin walled bar (2) axisymmetrical two at fin (201)；The fin (201) and thin-walled
The intersection of bar (2) is rounding off.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710052604.4A CN106945850B (en) | 2017-01-24 | 2017-01-24 | Satellite load wrapped type prestress thin-wall conical gravity gradient rod |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710052604.4A CN106945850B (en) | 2017-01-24 | 2017-01-24 | Satellite load wrapped type prestress thin-wall conical gravity gradient rod |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106945850A true CN106945850A (en) | 2017-07-14 |
| CN106945850B CN106945850B (en) | 2021-07-02 |
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ID=59465784
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710052604.4A Active CN106945850B (en) | 2017-01-24 | 2017-01-24 | Satellite load wrapped type prestress thin-wall conical gravity gradient rod |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109747864A (en) * | 2018-12-24 | 2019-05-14 | 深圳航天东方红海特卫星有限公司 | A kind of gravity gradient satellite based on increasing material manufacturing |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3640487A (en) * | 1967-07-13 | 1972-02-08 | Gen Electric | Vertical orientation device |
| CN1189803A (en) * | 1996-03-20 | 1998-08-05 | 国家空间研究中心 | Improvements to observation or telecommunication satellites |
| CN101823564A (en) * | 2010-03-31 | 2010-09-08 | 北京航空航天大学 | Super-elasticity coiled space-developable mechanism using precision U hinge |
| US20120146880A1 (en) * | 2010-12-08 | 2012-06-14 | Deutsches Zentrum Fuer Luft- Und Raumfahrt E.V | Self-Deploying Helical Antenna |
| CN103693212A (en) * | 2013-12-06 | 2014-04-02 | 上海卫星工程研究所 | Controlled-unfolding coiled stretching arm for unfolding satellite load |
| CN103693217A (en) * | 2013-12-06 | 2014-04-02 | 上海卫星工程研究所 | Retractable spatial stretching arm for satellite |
-
2017
- 2017-01-24 CN CN201710052604.4A patent/CN106945850B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3640487A (en) * | 1967-07-13 | 1972-02-08 | Gen Electric | Vertical orientation device |
| CN1189803A (en) * | 1996-03-20 | 1998-08-05 | 国家空间研究中心 | Improvements to observation or telecommunication satellites |
| CN101823564A (en) * | 2010-03-31 | 2010-09-08 | 北京航空航天大学 | Super-elasticity coiled space-developable mechanism using precision U hinge |
| US20120146880A1 (en) * | 2010-12-08 | 2012-06-14 | Deutsches Zentrum Fuer Luft- Und Raumfahrt E.V | Self-Deploying Helical Antenna |
| CN103693212A (en) * | 2013-12-06 | 2014-04-02 | 上海卫星工程研究所 | Controlled-unfolding coiled stretching arm for unfolding satellite load |
| CN103693217A (en) * | 2013-12-06 | 2014-04-02 | 上海卫星工程研究所 | Retractable spatial stretching arm for satellite |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109747864A (en) * | 2018-12-24 | 2019-05-14 | 深圳航天东方红海特卫星有限公司 | A kind of gravity gradient satellite based on increasing material manufacturing |
| CN109747864B (en) * | 2018-12-24 | 2022-04-22 | 深圳航天东方红海特卫星有限公司 | Gravity gradient satellite based on additive manufacturing |
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| Publication number | Publication date |
|---|---|
| CN106945850B (en) | 2021-07-02 |
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