CN109515760A - Spacecraft driving mechanism - Google Patents
Spacecraft driving mechanism Download PDFInfo
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- CN109515760A CN109515760A CN201811492415.XA CN201811492415A CN109515760A CN 109515760 A CN109515760 A CN 109515760A CN 201811492415 A CN201811492415 A CN 201811492415A CN 109515760 A CN109515760 A CN 109515760A
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- 238000000034 method Methods 0.000 description 8
- 238000010586 diagram Methods 0.000 description 5
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- 238000010521 absorption reaction Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
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- 230000015572 biosynthetic process Effects 0.000 description 1
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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
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
-
- 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
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
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- Engineering & Computer Science (AREA)
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- Aviation & Aerospace Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Photovoltaic Devices (AREA)
Abstract
A kind of spacecraft driving mechanism, comprising: shell, rotating device, fixed limiting device and rotating limit device.The first end of the shell with the spacecraft for connecting.The rotating device is assemblied in the second end of the shell, and can rotate around the geometric center of the shell.The fixed limiting device assembly is on the housing.The rotating limit device is assemblied on the rotating device, when the rotating device rotates to first angle around the geometric center of the shell, the first detent mode is between the rotating limit device and the fixed limiting device, the rotating device rotates to around the geometric center of the shell and is in the second detent mode when second angle between the rotating limit device and the fixed limiting device.Driving mechanism provided by the present application can guarantee that the rotating device can rotate at least one circumference while guaranteeing that the rotating device safely rotates within the scope of certain security standpoint.
Description
Technical field
The present invention relates to spacecraft fields, more particularly to a kind of driving mechanism of spaceborne driving expansion class device.
Background technique
With the fast development of small-business satellite, the driving expansion class mechanism on satellite needs to meet at low cost, reliable
The high requirement of property, will also meet in-orbit electrical transmission and the function to day opposite direction.Such as the solar wing driving mechanism on satellite needs
While driving solar wing rotation, the cable for preventing it internal, which excessively reverses, to be caused to damage.
Existing spacecraft driving mechanism mainly includes that motor, harmonic drive, slip ring etc. are used as electrical transmission component.
Wherein, the higher cost of slip ring, when cable is less, standby slip ring necessity is little, and reliability is turned round not as good as cable
The driving mechanism that makes the transition is reliable.Also, the driving mechanism quality of this scheme is larger, and axial dimension is also larger.
It would therefore be desirable to a kind of new spacecraft driving mechanism, to solve the above technical problems.
Summary of the invention
The application's is designed to provide a kind of new spacecraft driving mechanism, with solve the driving mechanism of the prior art at
The problems such as this is higher, reliability is insufficient, quality is larger and size is larger.
The one side of the application proposes a kind of spacecraft driving mechanism, may include: shell, and the first end of the shell is used
It is connect in the spacecraft；Rotating device, the rotating device are assemblied in the second end of the shell, and can be around described
The geometric center of shell rotates；Fixed limiting device, assembly is on the housing；And rotating limit device, it is assemblied in described
On rotating device, when the rotating device rotates to first angle around the geometric center of the shell, the rotary spacing dress
It sets in the first detent mode between the fixed limiting device, the rotating device is revolved around the geometric center of the shell
It goes to and is in the second detent mode when second angle between the rotating limit device and the fixed limiting device.
By assembling the rotating limit device on rotating device, in rotating device rotation, the rotation limit
Position device cooperates jointly with the fixed limiting device, the rotation of the rotating device can be limited in a certain range.
In addition, the structure of this limiting rotating angle is simple, it can contribute to reduce product quality, shorten the ruler of the driving mechanism
It is very little, to advantageously reduce cost.
In some embodiments, the driving mechanism may further include motor, for driving the rotating device to enclose
Geometric center around the shell rotates.By the way that motor is integrated in inside driving mechanism, it can reduce other transmission parts, from
And be conducive to reduce driving mechanism size.
In some embodiments, the difference of the first angle and the second angle can be not less than 360 °.Described turn
When the rotational angle of dynamic device covers a circumference, the components such as solar wing being assemblied on the rotating device equally be can be realized
360 ° of rotation increases energy absorption efficiency to guarantee to keep optimal to day angle always.
In some embodiments, the rotating limit device may include: detent block, be securely fitted in the rotating device
On；Rotary spacing block group, the rotary spacing block group include at least the first limit block and the second limit block, first limited block
It is assemblied on the rotating device with the second limited block, and can be around assembly point point rotation, wherein first limited block encloses
It contacts when turning to the first limited angular around assembly point with the detent block, second limited block turns to the around assembly
It is contacted when two limited angulars with the detent block.
Described two limited blocks can be rotated around the assembly point, and the constraint by the detent block, so that institute
It states rotating device and also realizes slewing area not less than 360 °.
In some embodiments, the rotating limit device may further include torsional spring, in first limit
Apply torsion on block or the second limited block, first limited block made to be fixed on the corresponding position of first limited angular,
Second limited block is set to be fixed on the corresponding position of second limited angular.
By the way that torsional spring is added in the rotating limit device, so that described two limited blocks are without other external forces
When, it can be stuck on the detent block freely movable about dressing with point rotation, ensure that the rotating limit device is whole
Stability.
In some embodiments, the first detent mode may include: the fixed limiting device and first limit
Position block and second limited block contact, and first limited block is contacted with the detent block, second limited block and institute
Detent block is stated not contact；The second detent mode may include: the fixed limiting device and first limited block and institute
The contact of the second limited block is stated, and second limited block is contacted with the detent block, first limited block and the detent block
It does not contact.
It is withstood respectively in the first limited angular and the second limited angular with the detent block by described two limited blocks,
And withstood with the fixed limited block, allow the slewing area of the rotating device by the first limit of described two limited blocks
Angle processed and the second limited angular are adjusted.Realize the controllability of the rotating device maximum rotation range.
In some embodiments, the enclosure interior space can accommodate at least one cable.Realize enclosure interior
Cavity area will can satisfy the demand for loading cable.
In some embodiments, can be set on the end face that the first end of the shell is connect with the spacecraft for
The hole that at least one cable passes through.By the way that hole is arranged on the end surface, so that the cable of the enclosure interior can be with
It is communicated to the inside of the spacecraft.
In some embodiments, can be set on the contact surface that the first end of the shell is connect with the spacecraft can
For the first interface of at least one cable connection.Cable and hole can be reduced in such a way that setting interface substitutes hole
Between friction, increase the service life of cable.
In some embodiments, the rotating device may include connect solar wing second interface and for it is described extremely
The hole that few single line cable passes through.By second interface, solar wing can be connected on the rotating device, so that solar wing can
To be rotated with the rotating device.By the way that hole is arranged on it, it can make the cable inside the rotating device can
To be connected on the solar wing, to transmit electric energy.
Other feature will be set forth in part in the description in the application.By the elaboration, make the following drawings and
The content of embodiment narration becomes apparent for those of ordinary skills.Inventive point in the application can pass through
Practice is sufficiently illustrated using method described in detailed example discussed below, means and combinations thereof.
Detailed description of the invention
Exemplary embodiment disclosed in this application is described in detail in the following drawings.Wherein identical appended drawing reference is in attached drawing
Several views in indicate similar structure.Those of ordinary skill in the art will be understood that these embodiments be non-limiting,
Exemplary embodiment, the purpose that attached drawing is merely to illustrate and describes, it is no intended to it limits the scope of the present disclosure, other modes
Embodiment may also similarly complete the intention of the invention in the application.It should be appreciated that the drawings are not drawn to scale.Wherein:
Fig. 1 shows the usage scenario figure according to shown in some embodiments of the present application.
Fig. 2 shows the driving mechanism schematic diagrames according to shown in some embodiments of the present application.
Fig. 3 is the front view along the driving mechanism of the opposite direction of x-axis in Fig. 1.
Fig. 4 show driving mechanism described in Fig. 3 along the sectional view of Section A-A.
Fig. 5 show driving mechanism described in Fig. 4 along the sectional view of section B-B.
Fig. 6 show the schematic diagram when rotating device turns to the second detent mode.
Specific embodiment
Following description provides the specific application scene of the application and requirements, it is therefore an objective to those skilled in the art be enable to make
It makes and using the content in the application.To those skilled in the art, to the various partial modifications of the disclosed embodiments
Be it will be apparent that and without departing from the spirit and scope of the disclosure, the General Principle that will can be defined here
Applied to other embodiments and application.Therefore, the embodiment the present disclosure is not limited to shown in, but it is consistent most wide with claim
Range.
Term used herein is only used for the purpose of description specific example embodiments, rather than restrictive.For example, unless
Context is expressly stated otherwise, used herein above, singular " one ", "one" and "the" also may include plural form.
When used in this manual, the terms "include", "comprise" and/or " containing " are meant that associated integer, step, behaviour
Make, element and/or component exist, but be not excluded for other one or more features, integer, step, operation, element, component and/or
Group presence or can be added in the system/method other features, integer, step, operation, element, component and/or.
In view of being described below, the operation of the related elements of these features of the disclosure and other features and structure and
The economy of combination and the manufacture of function and component may be significantly raising.With reference to attached drawing, all these formation disclosure
A part.It is to be expressly understood, however, that the purpose that attached drawing is merely to illustrate and describes, it is no intended to limit the disclosure
Range.
Fig. 1 shows the usage scenario figure according to shown in some embodiments of the present application.Spacecraft 1 as shown in the figure does not limit to
The satellite shown in also may include other any equipment run in space, such as spaceship, space shuttle, rocket
Deng.Spacecraft 1 shown in FIG. 1 may include several driving expansion class mechanism.The driving unfolding mechanism may include rugosity
State and unfolded state respectively correspond different working conditions.For example, during the launch process, the driving of the spacecraft is unfolded
Mechanism may be at folded state to reduce the overall volume of the spacecraft 1, convenient for transmitting.In another example working in space
In the process, the driving unfolding mechanism may be at unfolded state to realize its function.The folding and expanding mechanism can wrap
Include solar wing 2 as shown in the figure.The solar wing 2 may be at folded state during spacecraft 1 emits, and enter space
When planned orbit, unfolded state may be at, the luminous energy absorbed is converted into electric energy and is transmitted to the spacecraft 1.One
In a little embodiments, the solar wing 2 can transfer electrical energy into the spacecraft after converting light energy into electric energy by cable
In 1.
It, may be at certain angle with sun light direct beam direction after the solar wing 1 is converted into unfolded state by folded state
Degree.Solar wing plane described in sunlight not direct projection at this time leads to the loss for absorbing luminous energy total amount.Therefore, it is necessary to driving mechanisms 3
It drives the solar wing 2 to be rotated within the scope of certain angle, the expansion plane of the solar wing 2 is allowed too as far as possible
Sunlight vertical irradiation is to increase light energy absorption amount.In some embodiments, the cable passes through the driving by the solar wing 2
Mechanism 3 is connected on the spacecraft 1.Wherein, the part of the cable connection spacecraft 1 is fixed relative to the spacecraft 1,
The part of the cable connection solar wing 2 is fixed relative to the solar wing 2.Since the solar wing 2 is relative to the space flight
Device 1 is rotated, therefore the cable may twist in the rotation process of the solar wing 2.Therefore, the driving
Mechanism 3 can be limited in the rotation angle of the solar wing 2 in a certain range, to prevent the cable from excessively reversing.
In some embodiments, the driving mechanism 3 can pass through software to the limitation of the rotation angle of the solar wing 2
It realizes.For example, the processor of the spacecraft 1 is when the rotation angle for detecting the solar wing 2 is greater than preset threshold, it can be with
Instruction is sent to executing agency to limit the further rotating to the solar wing 2 of driving mechanism 3.However, in order to prevent
Software is run in some cases occurs mistake, cannot prevent excessive rotation of the driving mechanism 3 to the solar wing 2, institute
Stating driving mechanism 3 may include hard lockable mechanism, so that the solar wing 2 can only be rotated in a certain range.
Fig. 2 shows the driving mechanism schematic diagrames according to shown in some embodiments of the present application.The driving mechanism 3 includes
Shell 10 and rotating device 12.The first end of the shell 10 and the spacecraft 1 can connect by the way that the contact surface 11 is fixed
It connects.The rotating device 12 is for connecting the solar wing 2, to drive the rotation of the solar wing 2.
The rotating device 12 can be assemblied in the second end of the shell 10, and can surround the geometry of the shell 10
Center rotating.In the embodiment depicted in figure 2, the shell 10 is nearly cylindrical structure, and geometric center is x-axis as shown in the figure.
In the present embodiment, the geometric center of the rotating device 12 can be overlapped with the x-axis, and therefore, the rotating device 12 encloses
Around the geometric center of the shell 10 or the geometric center rotation of the rotating device 12.It should be noted that the rotation
Device 12 can be assemblied in the second end of the shell 10 with any assembly method, described in other specific embodiments
The geometric center of rotating device 12 might not be overlapped with the geometric center of the shell 10.
The driving mechanism 3 may further include motor 17.The motor 17 can drive the rotating device 12 to enclose
It is rotated around its geometric center.
The inner space of the shell 10 can accommodate at least one cable.In some embodiments, the shell 10
Hole 18 can be set on contact surface 11, so that the cable is passed through from the inner space of the shell 10 and is connected to described
In spacecraft 1.In some embodiments, described hole 18 also could alternatively be cable interface (first interface).The cable can
To be connected on the first interface in the inner space of the shell 10, by the first interface to the spacecraft 1
Transmit electric energy.
The driving mechanism 3 can also include lockable mechanism 19, for the maximum rotation range to the rotating device 12
It is limited.The lockable mechanism 19 may include the fixation limiting device 13 being assemblied on the shell 10 and be assemblied in institute
State the rotating limit device on rotating device 12.The fixed limiting device 13 is arranged on the shell 10, the rotation limit
Position device is arranged on the rotating device 12 and rotates with it.In some embodiments, the rotation model of the rotating device 12
It encloses and is limited in an angular interval, including the angle upper bound and angle lower bound.The angle is turned in the rotating device 12
When spending the upper bound, the rotating limit device can be contacted with the fixed limiting device 13.The fixed limiting device 13 is by applying
The resistance being added on the rotating limit device limits the further rotation of the rotating device 12, the fixed limit dress described at this time
Set 13 and the rotating limit device be in the first detent position.Similarly, the fixed limiting device 13 is described by being applied to
Resistance on rotating limit device limits further rotation of the rotating device 12 when reaching the angle lower bound, at this time institute
It states fixed limiting device 13 and the rotating limit device is in the second detent position.
In the embodiments illustrated in the figures, the rotating limit device may include detent block 14, the first limited block 15a with
And the second limited block 15b.The first limited block 15a and the second limited block 15b collectively form rotary spacing block group.It should be noted that
, the limited block group can not only include the first limited block 15a and the second limited block 15b, may be implemented as
It may include more standoff features in the case where the function of first limited block 15a and the second limited block 15b.It is shown in the figure
Embodiment in, the detent block 14 is assemblied in the outer rim of the rotating device 12, the limit of the first limited block 15a and second
Block 15b hinge mounted is on the rotating device 12 and the inside of the detent block 14.The first limited block 15a and second
Limited block 15b can be rotated around its hinge joint 16.The first limited block 15a or the second limited block 15b is surrounding the hinge
Contact 16 can be blocked when rotating to a certain extent by the detent block 14 to limit its and further rotate.Such as the implementation in figure
In example, the first limited block 15a and the second limited block 15b are symmetrical L-shaped structure, in its rotation process, L-shaped structure
Short side can push up on the detent block 14 and can not continue to rotate.The first limited block 15a and the second limited block 15b with
During the rotating device 12 rotates, the long side of L-shaped structure can push up the fixed limiting device 13, thus realization pair
The limitation of 12 slewing area of rotating device (detailed description is see Fig. 5 and its associated description).The top first limited block 15a
Corresponding first limited angular when to the detent block 14, corresponding second when the top the second limited block 15b is to the detent block 14
Limited angular.
Fig. 3 is the front view along the driving mechanism of the opposite direction of x-axis in Fig. 1.It is filled as shown in the figure for the rotation
Set 12.It may include connecting the second interface 21 of the solar wing 2 and being passed through for the cable on the rotating device 12
Hole 22.The second interface 21 may include the flange-interface shown in figure for being distributed in the rotating mechanism outer circumferential area
(second interface 21 is directed toward one of flange-interface in figure).The hole 22 can allow the cable inside the shell 10 to pass through simultaneously
It is connected on the solar wing 2.In some embodiments, the hole 22 can also be replaced with cable interface (third interface).Institute
Stating the cable inside shell 10 may be coupled on the third interface, be obtained by the third interface from the solar wing 2
Electric energy.
Fig. 4 show driving mechanism described in Fig. 3 along the sectional view of Section A-A.Sky inside shell 10 shown in figure
Cavity region 31.It may include more cables as shown in the figure in the cavity area 31 after driving mechanism assembly.It is described
More cables enter in the cavity area 31 from the hole 18, and the cavity area 31 is pierced by from the hole 22.By
It is connected on the spacecraft 1 in the contact surface 11 comprising hole 18, the rotating device 12 comprising hole 22 is revolved around its geometric center
Turn, the cable is fixing end in one end of adjacent pores 18, is turning end in one end of adjacent pores 22, when rotating device 12 rotates
It twists.
Fig. 5 show driving mechanism described in Fig. 4 along the sectional view of section B-B.Rotating limit device shown in figure into
One step includes torsional spring 41.The torsional spring 41 is used for by applying torsion to the first limited block 15a and the second limited block 15b,
So that the first limited block 15a or the second limited block 15b blocks in the case where not by fixed 13 active force of limiting device
Detent block 14 is stated in residence, i.e., so that the first limited block 15a is fixed on the first limited angular, the second limited block 15b is fixed on second
Limited angular.
The angle upper bound is rotated to as shown in the figure for the first detent mode namely the rotating device 12.In figure, described turn
Dynamic device 12 is rotated to state as shown in the figure in the counterclockwise direction.In the course of rotation, the first limited block 15a
The long side of L-shaped structure is pushed up first has arrived the fixed limiting device 13.Since the driving force of the rotating device 12 is much larger than torsion
Spring 41 is applied to the torsion on the first limited block 15a, and the first limited block 15a can be turned to around the hinge joint 16
Position as shown in the figure.Torsional spring 41 is compressed at this time, and the torsion being applied on the first limited block 15a can make described
One limited block 15a is restored to the first limit angles when fixed limiting device 13 and the first limited block 15a is disengaged
It spends (withstanding the detent block 14).
As the rotating device 12 continues to rotate counterclockwise, second limited block is arrived on the fixed top of limiting device 13
The long side (state as shown in the figure) of the L-shaped structure of 15b.By the second limited block 15b L-shaped structure short side with institute
It states detent block 14 to withstand (i.e. in the second limited angular) and can not rotate around the hinge joint 16 again, so second limit
Position block 15b is blocked by the fixed limiting device 13 together with entire rotating device 12 and can not be continued to rotate counterclockwise.
When the rotating device 12 is rotated clockwise from diagram state, torsion of the first limited block 15a in torsional spring 41
Power effect is lower to be rotated clockwise around the hinge joint 16, reaches the first limitation when disengaging with the fixed limited block 13
Angle (is contacted with the detent block 14).
Fig. 6 show the schematic diagram when rotating device turns to the second detent mode.Rotating device 12 in Fig. 5 after
Continuing can reach the second detent mode shown in fig. 6 when being rotated in the clockwise direction.Wherein, the limit of the first limited block 15a and second
The motion mode of position block 15b is identical with Fig. 5, and details are not described herein.
The rotating device 12 is rotated clockwise from the first detent mode, the second limited block 15b with it is described solid
When fixing limit block 13 is from disengaging to being contacted again, the rotating device 12 has been rotated through 360 ° and (ignores second limit
The influence of the long hem width degree of the L-shaped structure of block 15b).When the second limited block 15b continues to rotate to the second detent mode,
Already exceed 360 ° of certain angles (offset angle, such as 3 °, 5 °, 10 °).In the L-shaped structure for considering the second limited block 15b
When long side widths affect, as long as guaranteeing the influence of rotation of the width to the rotating device 12 no more than the compensation angle
Degree, that is, can guarantee that the angle when rotating device 12 turns to the second detent mode from the first detent mode is not small
In 360 °.
Correspondingly, the rotational angle range for the solar wing 2 being assemblied on the rotating device is nor less than 360 °.In this way may be used
To guarantee the spacecraft 1 under any posture, the solar wing 2 can be adjusted and reach a target angle, so that it is just
Maximum is reached to the area of sunlight, to increase the inversion quantity of electric energy.
In conclusion after reading this detailed disclosures, it will be understood by those skilled in the art that aforementioned detailed disclosure
Content can be only presented in an illustrative manner, and can not be restrictive.Although not explicitly described or shown herein, this field skill
Art personnel are understood that improve and modify it is intended to include the various reasonable changes to embodiment.These change, improve and
It modifies and is intended to be proposed by the disclosure, and in the spirit and scope of the exemplary embodiment of the disclosure.
In addition, certain terms in the application have been used for describing implementation of the disclosure example.For example, " one embodiment ",
" embodiment " and/or " some embodiments " means to combine the special characteristic of embodiment description, and structure or characteristic may include
In at least one embodiment of the disclosure.Therefore, it can emphasize and it is to be understood that right in the various pieces of this specification
Two or more references of " embodiment " or " one embodiment " or " alternate embodiment " are not necessarily all referring to identical implementation
Example.In addition, special characteristic, structure or characteristic can be appropriately combined in one or more other embodiments of the present disclosure.
It should be appreciated that in the foregoing description of embodiment of the disclosure, in order to help to understand a feature, originally for simplification
Disclosed purpose, the application sometimes combine various features in single embodiment, attached drawing or its description.Alternatively, the application is again
Be by various characteristic dispersions in multiple the embodiment of the present invention.However, this be not to say that the combination of these features be it is necessary,
Those skilled in the art are entirely possible to come out a portion feature extraction as individual when reading the application
Embodiment understands.That is, embodiment in the application it can be appreciated that multiple secondary embodiments integration.And it is each
The content of secondary embodiment is also to set up when being less than individually all features of aforementioned open embodiment.
In some embodiments, the quantity or property for certain embodiments of the application to be described and claimed as are expressed
The number of matter is interpreted as in some cases through term " about ", " approximation " or " substantially " modification.For example, unless otherwise saying
Bright, otherwise " about ", " approximation " or " substantially " can indicate ± 20% variation of the value of its description.Therefore, in some embodiments
In, the numerical parameter listed in written description and the appended claims is approximation, can be tried according to specific embodiment
Scheme the required property obtained and changes.In some embodiments, numerical parameter should be according to the quantity of the effective digital of report simultaneously
It is explained by the common rounding-off technology of application.Although illustrating that some embodiments of the application list broad range of numerical value
Range and parameter are approximations, but numerical value reported as precisely as possible is all listed in specific embodiment.
Herein cited each patent, patent application, the publication and other materials of patent application, such as article, books,
Specification, publication, file, article etc. can be incorporated herein by reference.Full content for all purposes, in addition to
Its relevant any prosecution file history, may or conflicting any identical or any possibility inconsistent with this document
On any identical prosecution file history of the restrictive influence of the widest range of claim.Now or later and this document
It is associated.For example, if in description, definition and/or the use of term associated with any included material and this
The relevant term of document, description, definition and/or between there are it is any inconsistent or conflict when, be using the term in this document
It is quasi-.
Finally, it is to be understood that the embodiment of application disclosed herein is the explanation to the principle of the embodiment of the application.
Other modified embodiments are also within the scope of application.Therefore, herein disclosed embodiment it is merely exemplary rather than
Limitation.Those skilled in the art can take alternative configuration according to the embodiment in the application to realize the invention in the application.
Therefore, embodiments herein is not limited to which embodiment accurately described in application.
Claims (10)
1. a kind of spacecraft driving mechanism characterized by comprising
Shell, the first end of the shell with the spacecraft for connecting；
Rotating device, the rotating device is assemblied in the second end of the shell, and can surround the geometric center of the shell
Rotation；
Fixed limiting device, assembly is on the housing；And
Rotating limit device is assemblied on the rotating device, and the rotating device is rotated around the geometric center of the shell
When to first angle, the first detent mode, the rotation are between the rotating limit device and the fixed limiting device
Device rotates to the rotating limit device and the fixed limiting device when second angle around the geometric center of the shell
Between be in the second detent mode.
2. spacecraft driving mechanism according to claim 1, which is characterized in that further comprise: motor, for driving
The geometric center that rotating device is stated around the shell rotates.
3. spacecraft driving mechanism according to claim 1, which is characterized in that the first angle and the second angle
Difference be not less than 360 °.
4. spacecraft driving mechanism according to claim 1, which is characterized in that the rotating limit device includes:
Detent block is securely fitted on the rotating device；
Rotary spacing block group, the rotary spacing block group include at least the first limit block and the second limit block, first limit
Block and the second limited block are assemblied on the rotating device, and can be rotated around assembly point point, wherein
First limited block contacts when turning to the first limited angular around assembly point with the detent block,
Second limited block contacts when turning to the second limited angular around assembly point with the detent block.
5. spacecraft driving mechanism according to claim 4, which is characterized in that the rotating limit device further comprises
Torsional spring is fixed on first limited block described for applying torsion on first limited block or the second limited block
The corresponding position of first limited angular makes second limited block be fixed on the corresponding position of second limited angular.
6. spacecraft driving mechanism according to claim 5, which is characterized in that
The first detent mode includes: that the fixed limiting device connects with first limited block and second limited block
Touching, and first limited block is contacted with the detent block, second limited block is not contacted with the detent block；
The second detent mode includes: that the fixed limiting device connects with first limited block and second limited block
Touching, and second limited block is contacted with the detent block, first limited block is not contacted with the detent block.
7. spacecraft driving mechanism according to claim 1, which is characterized in that the enclosure interior space can accommodate to
Few single line cable.
8. spacecraft driving mechanism according to claim 7, which is characterized in that the first end of the shell and the space flight
The hole passed through for at least one cable is provided on the end face of device connection.
9. spacecraft driving mechanism according to claim 7, which is characterized in that the first end of the shell and the space flight
The first interface at least one cable connection is provided on the contact surface of device connection.
10. spacecraft driving mechanism according to claim 7, which is characterized in that the rotating device includes the connection sun
The second interface of the wing and the hole passed through for at least one cable.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811492415.XA CN109515760B (en) | 2018-12-07 | 2018-12-07 | Spacecraft driving mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811492415.XA CN109515760B (en) | 2018-12-07 | 2018-12-07 | Spacecraft driving mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109515760A true CN109515760A (en) | 2019-03-26 |
| CN109515760B CN109515760B (en) | 2020-06-09 |
Family
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| CN201811492415.XA Active CN109515760B (en) | 2018-12-07 | 2018-12-07 | Spacecraft driving mechanism |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111591473A (en) * | 2020-05-07 | 2020-08-28 | 上海宇航系统工程研究所 | Oscillating solar cell array driving device |
| WO2023024203A1 (en) * | 2021-08-27 | 2023-03-02 | 重庆大学 | Sun-oriented directional solar wing driving device |
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| CN205752913U (en) * | 2016-04-23 | 2016-11-30 | 范天荣 | One is rotatably connected device |
| CN206700173U (en) * | 2017-01-06 | 2017-12-05 | 合肥美亚光电技术股份有限公司 | The mechanical stop limiter and x-ray imaging equipment of x-ray imaging equipment |
| CN207455355U (en) * | 2017-12-11 | 2018-06-05 | 东莞市莱尔照明电器有限公司 | It is a kind of can 360 ° rotation shot-lights |
| CN207490089U (en) * | 2017-12-31 | 2018-06-12 | 宁波迪泰电子科技有限公司 | Marine satellite antenna position-limit mechanism |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| FR2719280B1 (en) * | 1994-05-02 | 1997-01-03 | Martin Marietta Corp | Spacecraft equipped with a device for progressive acceleration of solar panels. |
| CN205752913U (en) * | 2016-04-23 | 2016-11-30 | 范天荣 | One is rotatably connected device |
| CN206700173U (en) * | 2017-01-06 | 2017-12-05 | 合肥美亚光电技术股份有限公司 | The mechanical stop limiter and x-ray imaging equipment of x-ray imaging equipment |
| CN207455355U (en) * | 2017-12-11 | 2018-06-05 | 东莞市莱尔照明电器有限公司 | It is a kind of can 360 ° rotation shot-lights |
| CN207490089U (en) * | 2017-12-31 | 2018-06-12 | 宁波迪泰电子科技有限公司 | Marine satellite antenna position-limit mechanism |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111591473A (en) * | 2020-05-07 | 2020-08-28 | 上海宇航系统工程研究所 | Oscillating solar cell array driving device |
| WO2023024203A1 (en) * | 2021-08-27 | 2023-03-02 | 重庆大学 | Sun-oriented directional solar wing driving device |
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| Publication number | Publication date |
|---|---|
| CN109515760B (en) | 2020-06-09 |
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