CN106945850B - Satellite load wrapped type prestress thin-wall conical gravity gradient rod - Google Patents
Satellite load wrapped type prestress thin-wall conical gravity gradient rod Download PDFInfo
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- CN106945850B CN106945850B CN201710052604.4A CN201710052604A CN106945850B CN 106945850 B CN106945850 B CN 106945850B CN 201710052604 A CN201710052604 A CN 201710052604A CN 106945850 B CN106945850 B CN 106945850B
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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
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Abstract
The invention provides a satellite load wrapped type prestress thin-wall conical gravity gradient rod which is characterized by being applied to the field of spacecrafts and comprising a satellite, a thin-wall rod, a load and a small-end frame. The small-end frame comprises a baffle I, a baffle II and a rotating shaft. The thin-wall rod is integrally conical, the end with the larger diameter of the thin-wall rod is a large end, and the end with the smaller diameter of the thin-wall rod is a small end. The load is mounted on the small end frame. The large end of the thin-wall rod is fixed on the side face of the satellite through a flange, and the small end of the thin-wall rod penetrates through the speed-limiting narrow opening and is fixed on a load. The invention has the advantages of simple structure, no redundant kinematic pair, and capability of keeping the large end of the rod fixed on the satellite relatively stable and effectively resisting external resistance. The gravity gradient rod can be stretched automatically after reaching the outer space without an additional driving device. The thin-walled rod can be flattened, so that high expansion ratio is realized.
Description
Technical Field
The invention relates to the technical field of space extension mechanisms, in particular to a satellite load wrapped type prestress thin-wall conical gravity gradient rod.
Background
When the space satellite orbits the earth, the earth center has different gravitations to the mass of each part of the satellite, and the resultant force of the gravitation and the centrifugal force is called gravity. The satellite can be simply divided into a mass m1 closer to the center of the earth and a mass m2 farther from the center of the earth, because m1 is closer to the center of the earth and thus receives more attractive force than centrifugal force, and the gravitational force is directed to the center of the earth, and m2 is farther from the center of the earth and thus receives less attractive force than centrifugal force, and the gravitational force is opposite to the center of the earth. The satellite midpoint O is zero gravity. Thereby creating a restoring moment about point O, i.e., a gravity gradient moment.
The gravity gradient moment is used for stabilizing the attitude of the satellite in space operation, and the magnitude of the moment is related to the difference of the rotational inertia of each axis of the satellite besides the height and the shape of the orbit. The larger the difference of the rotational inertia of each shaft is, the better the attitude stability is. The gravity gradient rod plays a key role in adjusting the rotational inertia, and the difference of the rotational inertia of each axis of the satellite can reach dozens of times or even more than one hundred times by extending out of the gravity gradient rod after the satellite enters the orbit. Finally, the minimum inertia axis of the satellite is stabilized in the direction of the local plumb line, and the maximum inertia axis of the satellite is stabilized in the direction of the normal line of the orbit plane. This state is the stable equilibrium attitude of the satellite.
With the development of aerospace technology, the space structure is becoming large and complex, but the storage space for the spacecraft to carry mass and payload is limited, and the mass and size of the rigid gravity gradient rod are greatly limited. The pole length of gravity gradient pole is a very big problem to accomodating to general satellite, and the gravity gradient pole that each country designed all makes the design under this basic prerequisite. The current gravity gradient rod pursues lighter weight, simple structure and small occupied space. The gravity gradient rod is required to be developed with high reliability, high expansion ratio, light weight, low power consumption and the like when being designed. Conventional rigid gravity gradient rods have exposed to a number of disadvantages in today's aerospace technology and aerospace environment.
Disclosure of Invention
The invention aims to provide a load wrapping type prestress thin-wall conical gravity gradient rod which has the advantages of high expansion ratio, self-expansion, light weight, high rigidity, high reliability and the like and is suitable for adjusting the posture of an on-orbit satellite. The problem of payload's storage space is limited, the difficult storage of gravity gradient pole is solved.
The technical scheme adopted for achieving the purpose of the invention is that the satellite load wrapped type prestress thin-wall conical gravity gradient rod is characterized by being applied to the field of spacecrafts and comprising a satellite, a thin-wall rod, a load and a small-end frame.
The tip frame includes baffle I, baffle II and pivot, baffle I and II symmetrical arrangement of baffle, install the pivot between baffle I and the baffle II. Baffle I and baffle II pass through horizontal pole fixed connection together, the one end of horizontal pole is fixed in on baffle I, and the other end is fixed in on baffle II. The transverse rod is provided with a speed-limiting narrow opening.
The thin-wall rod is integrally conical, the end with the larger diameter of the thin-wall rod is a large end, the end with the smaller diameter of the thin-wall rod is a small end, and the diameter between the small end and the large end of the thin-wall rod is in smooth transition. The thin-wall rod can be curled along the length direction and then restored to the original shape.
The load is arranged on the small-end frame through the rotating shaft and is located between the baffle I and the baffle II. The load may rotate about an axis of rotation.
The large end of the thin-wall rod is fixed on the satellite through a flange, and the small end of the thin-wall rod penetrates through the speed-limiting narrow opening to be fixed on the load.
Before the satellite enters a preset orbit, the thin-wall rod is in a contraction state, the small end of the thin-wall rod rotates around the rotating shaft along with the load to cover the load, the thin-wall rod is rolled into a flat shape at the moment until the small end frame is close to the satellite, so that the thin-wall rod cannot be further contracted, then the load is fixed through the locking mechanism, the load cannot rotate, and the thin-wall rod cannot be extended. After the satellite enters a preset orbit, the locking mechanism on the small-end frame is unlocked, so that the load can rotate, and the thin-wall rod is changed from a coiled contraction state to an extended state. The thin-wall rod is automatically and slowly unfolded through prestress, and the speed of the thin-wall rod in the unfolding process is kept moderate due to the action of the speed limiting narrow opening on the small-end frame. After the satellite is completely unfolded, the distance between the satellite and the small-end frame and the distance between the satellite and the load arranged on the small-end frame reach the maximum, and finally the satellite enters a normal working stage.
Further, the side wall of the thin-wall rod is provided with two convex edges which are symmetrical about the axis of the thin-wall rod. The junction of the convex edge and the thin-wall rod is in smooth transition.
The invention has the advantages of simple structure, no redundant kinematic pair, relative stability of the rod fixed on the satellite at the large end, and effective resistance to external resistance such as space debris and radiation. The gravity gradient rod can be automatically stretched without power and driving devices such as electric power, chemical energy, pneumatic power and the like after reaching the outer space. The thin-walled rod can be flattened, so that high expansion ratio is realized. The thin-wall rod adopts a thin-wall conical structure, so that the mass of the thin-wall rod is greatly lower than that of the cylindrical rod, and the whole mass is reduced because a power source and a related driving device are not needed.
Drawings
FIG. 1 is a schematic view of the present invention in a contracted state;
FIG. 2 is a schematic diagram of the present invention in an extended state;
FIG. 3 is a schematic view of a small end frame;
FIG. 4 is a schematic cross-sectional view of a thin wall rod; .
In the figure: the device comprises a satellite 1, a thin-wall rod 2, a load 3, a small-end frame 4, a rotating shaft 401, a speed-limiting narrow opening 402 and a flange 5.
Detailed Description
The present invention is further illustrated by the following examples, but it should not be construed that the scope of the above-described subject matter is limited to the following examples. Various substitutions and alterations can be made without departing from the technical idea of the invention and the scope of the invention is covered by the present invention according to the common technical knowledge and the conventional means in the field.
A satellite load wrapped type prestress thin-wall conical gravity gradient rod is characterized by being applied to the field of spacecrafts and comprising a satellite 1, a thin-wall rod 2, a load 3 and a small-end frame 4.
The small-end frame 4 comprises a baffle I403, a baffle II 404 and a rotating shaft 401, wherein the baffle I403 and the baffle II 404 are symmetrically arranged, and the rotating shaft 401 is arranged between the baffle I403 and the baffle II 404. The baffle I403 and the baffle II 404 are fixedly connected together through a cross rod, one end of the cross rod is fixed on the baffle I403, and the other end of the cross rod is fixed on the baffle II 404. The cross bar is provided with a speed limiting narrow opening 402.
The thin-wall rod 2 is integrally conical, one end of the thin-wall rod 2 with the larger diameter is a large end, the other end of the thin-wall rod 2 with the smaller diameter is a small end, and the diameter between the small end and the large end of the thin-wall rod 2 is in smooth transition. The thin-walled rod 2 can be curled in the length direction and then restored to the original shape.
The load 3 is installed on the small-end frame 4 through the rotating shaft 401, and the load 3 is located between the baffle I403 and the baffle II 404. The load 3 can rotate about a rotation axis 401.
The large end of the thin-wall rod 2 is fixed on the satellite 1 through a flange 5, and the small end of the thin-wall rod 2 penetrates through the speed-limiting narrow opening 402 and is fixed on the load 3.
Before the satellite 1 enters a preset orbit, the thin-wall rod 2 is in a contraction state, the small end of the thin-wall rod 2 rotates around the rotating shaft 401 along with the load 3 to cover the load 3, at the moment, the thin-wall rod 2 is rolled into a flat shape until the small-end frame 4 is close to the satellite 1, so that the thin-wall rod 2 cannot be further contracted, and then the load 3 is fixed through the locking mechanism, so that the load 3 cannot rotate, and the thin-wall rod 2 cannot be extended. After the satellite 1 enters a preset orbit, the locking mechanism on the small end frame 4 is opened, so that the load 3 can rotate, and the thin-walled rod 2 is changed from a coiled contraction state to an extended state. The thin-wall rod 2 is automatically and slowly unfolded through prestress, and the speed of the unfolding process of the thin-wall rod 2 is kept moderate due to the action of the speed limiting narrow opening 402 on the small-end frame 4. After the satellite 1 is completely unfolded, the distance between the satellite 1 and the small-end frame 4 and the load 3 arranged on the small-end frame 4 reaches the maximum, and finally the satellite 1 enters a normal working stage.
The horizontal plane of the rotating shaft 401 is higher than the horizontal plane of the speed limiting narrow opening 402.
The side wall of the thin-wall rod 2 is provided with two convex ribs 201 which are symmetrical about the axis of the thin-wall rod 2. The junction of the convex edge 201 and the thin-wall rod 2 is in smooth transition.
Claims (1)
1. The satellite load wrapped type prestress thin-wall conical gravity gradient rod is characterized by being applied to the field of spacecrafts and comprising a satellite (1), a thin-wall rod (2), a load (3) and a small-end frame (4);
the small-end frame (4) comprises a baffle I (403), a baffle II (404) and a rotating shaft (401), the baffle I (403) and the baffle II (404) are symmetrically arranged, and the rotating shaft (401) is arranged between the baffle I (403) and the baffle II (404); the baffle I (403) and the baffle II (404) are fixedly connected together through a cross rod, one end of the cross rod is fixed on the baffle I (403), and the other end of the cross rod is fixed on the baffle II (404); a speed-limiting narrow opening (402) is formed in the cross bar;
the thin-wall rod (2) is integrally conical, the end with the larger diameter of the thin-wall rod (2) is a large end, the end with the smaller diameter of the thin-wall rod is a small end, and the diameter from the small end to the large end of the thin-wall rod (2) is in smooth transition; the thin-wall rod (2) can be curled along the length direction and then restored to the original shape;
the load (3) is arranged on the small-end frame (4) through a rotating shaft (401), and the load (3) is positioned between the baffle I (403) and the baffle II (404); the load (3) can rotate around a rotating shaft (401);
the large end of the thin-wall rod (2) is fixed on the satellite (1) through a flange (5), and the small end of the thin-wall rod (2) penetrates through the speed-limiting narrow opening (402) and is fixed on the load (3); the side wall of the thin-wall rod (2) is provided with two convex edges (201) which are symmetrical about the axis of the thin-wall rod (2); the junction of the convex edge (201) and the thin-wall rod (2) is in smooth transition;
before the satellite (1) enters a preset orbit, the thin-wall rod (2) is in a contraction state, the small end of the thin-wall rod (2) rotates around the rotating shaft (401) along with the load (3) to wrap the load (3), the thin-wall rod (2) is rolled into a flat shape at the moment until the small-end frame (4) is close to the satellite (1), so that the thin-wall rod (2) cannot be further contracted, and then the load (3) is fixed through the locking mechanism, so that the load (3) cannot rotate, and the thin-wall rod (2) cannot be extended; after the satellite (1) enters a preset orbit, the locking mechanism on the small-end frame (4) is unlocked, so that the load (3) can rotate, and the thin-wall rod (2) is changed from a coiled contracted state to an expanded state. The thin-wall rod (2) is automatically and slowly unfolded through prestress, and the speed of the thin-wall rod (2) in the unfolding process is kept moderate due to the action of the upper speed limiting narrow opening (402) of the small-end frame (4); after the fully unfolded satellite is completely unfolded, the distance between the satellite (1) and the small-end frame (4) and the distance between the satellite (1) and the load (3) arranged on the small-end frame (4) are maximized, and finally the satellite (1) enters a normal working stage.
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 CN106945850A (en) | 2017-07-14 |
| CN106945850B true CN106945850B (en) | 2021-07-02 |
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| Application Number | Title | Priority Date | Filing Date |
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| 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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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Citations (5)
| 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 |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE202010013085U1 (en) * | 2010-12-08 | 2012-03-12 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Self-expanding helix antenna |
-
2017
- 2017-01-24 CN CN201710052604.4A patent/CN106945850B/en active Active
Patent Citations (5)
| 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 |
| 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 |
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| CN106945850A (en) | 2017-07-14 |
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