CN113859592B - Zero-gravity balance unfolding and folding test device for cabin door of spacecraft and application method - Google Patents
Zero-gravity balance unfolding and folding test device for cabin door of spacecraft and application method Download PDFInfo
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- CN113859592B CN113859592B CN202111197723.1A CN202111197723A CN113859592B CN 113859592 B CN113859592 B CN 113859592B CN 202111197723 A CN202111197723 A CN 202111197723A CN 113859592 B CN113859592 B CN 113859592B
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- 238000000034 method Methods 0.000 title claims abstract description 34
- 238000012360 testing method Methods 0.000 title claims abstract description 31
- 230000005484 gravity Effects 0.000 claims abstract description 35
- 230000007246 mechanism Effects 0.000 claims description 86
- 229910000831 Steel Inorganic materials 0.000 claims description 46
- 239000010959 steel Substances 0.000 claims description 46
- 238000013016 damping Methods 0.000 claims description 12
- 230000000087 stabilizing effect Effects 0.000 claims description 12
- 230000008569 process Effects 0.000 claims description 10
- 238000005259 measurement Methods 0.000 claims description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention provides a spacecraft cabin door zero-gravity balance unfolding test device and a use method thereof. The invention has simple structure, simple and convenient operation, small rotation resistance, good gravity compensation effect and reliable balance state, ensures that the zero gravity balance unfolding and folding of the spacecraft cabin door can be effectively realized under the action of limited driving moment, and provides a new scheme for the ground zero gravity balance unfolding and folding test of the spacecraft cabin door.
Description
Technical Field
The invention relates to the technical field of space vehicles, in particular to a zero-gravity balance unfolding and folding test device for a cabin door of a space vehicle and a use method.
Background
When the spacecraft works in the space orbit, the gravitational environment of the spacecraft is very different from the surface of the earth, for example, the near-earth orbit spacecraft is almost in a weightlessness state when in orbit. For some spacecraft, when the spacecraft is on track, the cabin door of the spacecraft is required to be smoothly unfolded and folded in place on the track, so that a window is provided for the in-and-out cabin test of the subsequent astronauts and cargo load, and the reliability of a hinge mechanism for providing a driving moment for the cabin door unfolding and folding is certainly a core factor for restricting whether the spacecraft cabin door can be successfully unfolded and folded on the track or not although the zero gravity state of the track can compensate the resistance moment generated by the cabin door weight on the cabin door unfolding and folding.
The patent document with the publication number of CN103587720B discloses a folding and unfolding mechanism of a split type cabin door of a spacecraft, which is used for completing the opening and closing actions of the cabin door, has the functions of positioning and braking, and belongs to the technical field of space mechanisms. The unfolding and folding mechanism comprises a cabin door bulkhead, a cabin door girder, a cabin door lock, a left cabin door, a right cabin door, a cabin door heat-proof structure, a machine body heat-proof structure, a mechanism driving shafting, a cabin door hinge and a mechanism connecting rod assembly. The mechanism driving shafting comprises a stepping motor, a speed reducer, an absolute angle meter, an angle meter fixing seat, a left bearing seat, a right bearing seat, a bearing seat mounting plate, an angle meter coupling, a motor switching shaft, a supporting bearing and an adjusting ring. The mechanism connecting rod assembly comprises a special crank, a connecting rod, a cabin door hinge seat, a joint ball bearing and a pin shaft screw.
In order to ensure the smooth unfolding and folding of the cabin door when the spacecraft is on the track, the reliability of the cabin door unfolding and folding driving mechanism of the spacecraft must be ensured first, so that the reliability of the driving mechanism (hinge) for driving the cabin door to unfold and fold smoothly is required to be fully verified in a zero gravity state when the spacecraft is on the track in the ground development stage before the spacecraft is launched. Therefore, a set of aircraft cabin door zero-gravity balance unfolding and folding test tool with the characteristics of simple structure, convenient operation, full cabin door gravity compensation, small self-resistance moment of a rotating mechanism and the like needs to be designed and developed, and the reliability of smooth unfolding and folding of the aircraft cabin door driven by a driving mechanism (hinge) with the zero-gravity state set in place is fully verified, so that a new scheme is provided for a zero-gravity balance unfolding and folding test of the space aircraft cabin door.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a spacecraft cabin door zero gravity balance unfolding test device and a use method thereof.
The invention provides a spacecraft cabin door zero gravity balance folding and unfolding test device, which comprises a two-dimensional adjusting mechanism, a rotating mechanism, a hanging beam, a linear guide rail, an adjusting screw, a steel wire rope, an electronic scale counterweight and an installing screw, wherein the adjusting screw is arranged on the hanging beam;
the two-dimensional adjusting mechanism is connected with the top of the universal portal frame, the rotating mechanism is connected with the hanging beam, and the whole rotating mechanism and the hanging beam are connected with the two-dimensional adjusting mechanism; and a linear guide rail, an adjusting screw and a steel wire rope are arranged below the end part of the hanging beam.
Preferably, the two-dimensional adjusting mechanism performs two-dimensional manual adjustment in a plane through an X-direction manual adjusting device and a Y-direction manual adjusting device.
Preferably, the rotating mechanism consists of an upper flange, a deep groove ball bearing, a lining plate, a plane bearing, a lining plate, a cylinder body, a bearing retainer ring, a lower flange and a rotating shaft; the deep groove ball bearings are positioned at two ends of the plane bearing.
Preferably, the hanging beam is rigidly connected with the rotating mechanism through a flange.
Preferably, the linear guide rail at the end part of the hanging beam automatically moves according to the stress direction of the steel wire rope below the hanging beam, so as to find and reach the coaxiality of the steel wire rope and the hanging point of the cabin door.
The invention also provides a use method of the spacecraft cabin door zero-gravity balance folding test device, the method is applied to the spacecraft cabin door zero-gravity balance folding test device, and the method comprises the following steps:
step S1: the two-dimensional adjusting mechanism is connected with the top of the universal portal frame;
step S2: after precisely measuring and adjusting the rotating mechanism to reach the required verticality by adopting a laser tracker, placing theoretically calculated counterweights below two steel wire ropes of the hanging beam;
step S3: after the initial resistance moment and the process resistance moment of the rotation of the test hanging beam meet the requirements, removing the counterweight at the steel wire rope and formally connecting the cabin door of the spacecraft in the closed state;
step S4: before the cabin door is connected, two adjusting screws below the hanging beam are adjusted to leave an equal length adjusting allowance, and the electronic scale on the steel wire rope is in a zero position;
step S5: precisely measuring and adjusting the perpendicularity of the cabin door damping speed stabilizing mechanism to reach a required value by adopting a laser tracker;
step S6: by manual adjustment of the two-dimensional adjusting mechanism and the cabin door hanging point;
step S7: the reading of the two electronic scales reaches the theoretical requirement value by adjusting the adjusting screws at the upper ends of the steel wire ropes at the two ends;
step S8: after the state is precisely measured and adjusted in place, the zero gravity balance unfolding and folding are performed under the driving of the hinge of the cabin door driving mechanism of the spacecraft.
Preferably, the step S1 further includes that the rotating mechanism is connected with the hanging beam flange plate through a lower flange, and then is integrally connected with the central flange surface of the bottom surface of the two-dimensional adjusting mechanism through a flange at the upper end of the rotating mechanism.
Preferably, the step S2 further includes adopting a precision chest expander to slowly and smoothly pull the hanging beam for one circle along the tangential direction of the rotation of the hanging beam at the fixing position of the steel wire rope at the end part of the hanging beam, and testing the initial resistance moment and the process resistance moment of the rotation of the hanging beam.
Preferably, the step S4 further includes connecting two steel wires with hanging points at two ends of the cabin door, and slightly tightening the steel wires at two ends by adjusting the screw, where the electronic scale is in the same reading.
Preferably, the perpendicularity of the steel wire rope connecting the cabin door hanging point in the process of adjusting the adjusting screw in the step S7 is automatically adjusted in place through the movement of the linear guide rail.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention provides a spacecraft cabin door zero gravity balance unfolding and folding test device and a use method thereof, and the tool has the characteristics of simple structure, convenient operation, full cabin door gravity compensation, small self resistance moment and the like;
2. the invention can effectively realize the zero gravity balance state of the aircraft cabin door and fully verify the reliability of the hinge driving of the driving mechanism to drive the aircraft cabin door to be unfolded and folded under the zero gravity state;
3. the invention provides a new scheme for the zero gravity balance folding test of the spacecraft cabin door.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic view of a spacecraft door of the present invention deployed in a 90 degree position in a zero gravity position;
FIG. 2 is a schematic view of a zero gravity deployment and retraction tooling for a spacecraft door according to the present invention;
fig. 3 is a schematic view of a rotating mechanism of a zero gravity deployment and retraction tooling for a spacecraft door according to the present invention.
Wherein:
first lining plate 23 of two-dimensional adjusting mechanism 10
Plane bearing 24 of X-direction manual adjusting device 11
Second lining plate 25 of Y-direction manual adjusting device 12
Rotary mechanism 20 barrel 26
Bearing retainer 27 of upper flange 21
Lower flange 28 of deep groove ball bearing 22
Rotating shaft 29
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
The invention provides a spacecraft cabin door zero gravity balance folding and unfolding test device and a use method thereof, wherein a tool comprises a two-dimensional adjusting mechanism 10, a rotating mechanism 20, a hanging beam, a linear guide rail, an adjusting screw, a steel wire rope, an electronic scale counterweight and a mounting screw; when the device is used, the two-dimensional adjusting mechanism 10 is connected with the top of the universal portal frame, the rotating mechanism 20 is connected with the flange plate of the hanging beam through the lower flange 28, and then the whole device is connected with the central flange surface of the bottom surface of the two-dimensional adjusting mechanism 10 through the flange at the upper end of the rotating mechanism 20, and the laser tracker is adopted to precisely measure and adjust the rotating mechanism 20 to achieve the required verticality; and then installing a linear guide rail, an adjusting screw and a steel wire rope below the end part of the hanging beam, loading the theoretically calculated counter weights below the two steel wire ropes, slowly and smoothly pulling the hanging beam for one circle along the tangential direction of rotation of the hanging beam at the fixed position of the steel wire rope at the end part of the hanging beam by adopting a precise chest expander, and detaching the counter weights at the steel wire ropes and formally connecting the cabin door of the spacecraft in the closed state after the initial resistance moment and the process resistance moment for testing the rotation of the hanging beam meet the requirements.
Before the cabin door is connected, two adjusting screws below the hanging beam are firstly adjusted to leave an equal length adjusting allowance, the electronic scales on the steel wire ropes are all in zero positions, the two steel wire ropes are respectively connected with hanging points at two ends of the cabin door, the steel wire ropes at the two ends are slightly tensioned through the adjusting screws, and the electronic scales are in the same reading; under the condition that the verticality of the cabin door damping speed stabilizing mechanism is adjusted in place, the cabin door damping speed stabilizing mechanism is adjusted through three jacks below the cabin body, the two-dimensional adjusting mechanism 10 and the manual adjustment of cabin door hanging points are further conducted, the coaxiality of the rotating mechanism 20, the cabin door hanging points and the damping speed stabilizing mechanism is guaranteed to meet the requirement of accurate measurement indexes, finally, the two electronic scales are enabled to read out to reach theoretical requirement values through adjusting the adjusting screws at the upper ends of the steel wire ropes at the two ends, and the verticality of the steel wire ropes connected with the cabin door hanging points can be automatically adjusted in place through the movement of the linear guide rails in the adjusting screw adjusting process. After the state is precisely measured and adjusted in place, zero gravity balance unfolding and folding of the spacecraft cabin door under the drive of the damping speed stabilizing mechanism can be realized, and the damping speed stabilizing mechanism is a hinge in the embodiment.
The two-dimensional adjusting mechanism 10 can complete two-dimensional manual adjustment in a plane through the X-direction manual adjusting device 11 and the Y-direction manual adjusting device 12, so that coaxiality of the rotating mechanism 20, a cabin door hanging point and a damping speed stabilizing mechanism can be effectively realized, and coaxiality deviation is avoided to generate a resisting moment for cabin door unfolding and folding.
The rotating mechanism 20 consists of an upper flange 21, a deep groove ball bearing 22, a first lining plate 23, a plane bearing 24, a second lining plate 25, a cylinder 26, a bearing retainer 27, a lower flange 28 and a rotating shaft 29. The rotating mechanism 20 has good axial and radial bearing capacity on the rotating shaft 29, and the two deep groove ball bearings 22 are arranged at the two ends of the plane bearing 24, so that the deflection deformation of the rotating shaft 29 when being subjected to unbalanced load is effectively avoided, and the rotating mechanism 20 can bear smaller rotation resistance moment.
The rigid connection mode of the flange between the hanging beam and the rotating mechanism 20 ensures that the rotating track of the hanging beam can still be kept in the same plane even if the hanging beam is connected with the cabin door and has certain unbalanced load under the application state of the theoretical counterweight, thereby avoiding the bending of the hanging beam to bring resistance moment to the unfolding and folding of the cabin door.
The linear guide rail at the end part of the hanging beam can move automatically according to the stress direction of the steel wire rope below the linear guide rail, and the coaxiality of the steel wire rope and a cabin door hanging point is reliably searched and reached, so that the increase of the resistance moment of cabin door unfolding and folding caused by the fact that the inclined hanging force of the steel wire rope generates torque on the damping speed stabilizing mechanism is effectively avoided.
The use of adjusting screw and electronic scale can reliably guarantee the balance of suspension system to cabin door theoretical gravity through the monitoring of electronic scale registration at the in-process of effectively adjusting wire rope taut length to avoid wire rope taut force unable balanced cabin door gravity to lead to the moment of resistance increase that the cabin door was unfolded and received.
A method for using a spacecraft cabin door zero gravity balance unfolding test device comprises the following steps:
step S1: the two-dimensional adjusting mechanism 10 is connected with the top of the universal portal frame, and the rotating mechanism 20 is connected with the hanging beam flange plate through the lower flange 28 and then integrally connected with the central flange surface of the bottom surface of the two-dimensional adjusting mechanism 10 through the upper flange of the rotating mechanism 20.
Step S2: after the laser tracker is adopted to precisely measure and adjust the rotating mechanism 20 to achieve the required verticality, a theoretically calculated counter weight is placed below two steel wires of the hanging beam, a precise chest expander is adopted to slowly and smoothly pull the hanging beam for one circle along the tangential direction of the rotation of the hanging beam at the fixed position of the steel wires at the end part of the hanging beam, and the initial resistance moment and the process resistance moment of the rotation of the hanging beam are tested.
Step S3: and after the initial resistance moment and the process resistance moment for testing the rotation of the hanging beam meet the requirements, removing the counterweight at the steel wire rope, and formally connecting the cabin door in the closed state of the spacecraft.
Step S4: before connecting the cabin door, adjusting two adjusting screws below the hanging beam to leave an equal length adjusting allowance, arranging the electronic scale on the steel wire ropes at zero positions, connecting the two steel wire ropes with hanging points at two ends of the cabin door respectively, slightly tensioning the steel wire ropes at two ends through the adjusting screws, and arranging the electronic scale at the same reading.
Step S5: and precisely measuring and adjusting the perpendicularity of the cabin door damping speed stabilizing mechanism to reach a required value by adopting a laser tracker.
Step S6: by manually adjusting the two-dimensional adjusting mechanism 10 and the cabin door hanging point, the coaxiality of the rotating mechanism 20, the cabin door hanging point and the damping speed stabilizing mechanism is ensured to meet the requirement of a precise measurement index.
Step S7: the two electronic scales can read to reach the theoretical requirement value by adjusting the adjusting screws at the upper ends of the steel wire ropes at the two ends, and the verticality of the steel wire rope connected with the cabin door hanging point can be automatically adjusted in place by the movement of the linear guide rail in the adjusting screw adjusting process.
Step S8: after the state is precisely measured and adjusted in place, zero gravity balance unfolding and folding under the driving of the hinge of the cabin door driving mechanism of the spacecraft can be realized.
The invention provides a spacecraft cabin door zero gravity balance unfolding and folding test device and a use method thereof, and the tool has the characteristics of simple structure, convenient operation, full cabin door gravity compensation, small self resistance moment and the like; the zero gravity balance state of the aircraft cabin door can be effectively realized, and the reliability of the hinge of the driving mechanism for driving the aircraft cabin door to be unfolded and folded under the zero gravity state is fully verified; a new scheme is provided for the zero-gravity balance folding test of the spacecraft cabin door.
Those skilled in the art will appreciate that the invention provides a system and its individual devices, modules, units, etc. that can be implemented entirely by logic programming of method steps, in addition to being implemented as pure computer readable program code, in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers, etc. Therefore, the system and various devices, modules and units thereof provided by the invention can be regarded as a hardware component, and the devices, modules and units for realizing various functions included in the system can also be regarded as structures in the hardware component; means, modules, and units for implementing the various functions may also be considered as either software modules for implementing the methods or structures within hardware components.
In the description of the present application, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and are not to be construed as limiting the present application.
The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the invention. The embodiments of the present application and features in the embodiments may be combined with each other arbitrarily without conflict.
Claims (9)
1. The application method of the space vehicle cabin door zero gravity balance folding test device is characterized by comprising a two-dimensional adjusting mechanism (10), a rotating mechanism (20), a hanging beam, a linear guide rail, an adjusting screw, a steel wire rope, an electronic scale counterweight and an installing screw;
the two-dimensional adjusting mechanism (10) is connected with the top of the universal portal frame, the rotating mechanism (20) is connected with the hanging beam, and the whole rotating mechanism (20) and the hanging beam are connected with the two-dimensional adjusting mechanism (10); a linear guide rail, an adjusting screw and a steel wire rope are arranged below the end part of the hanging beam;
the method comprises the following steps:
step S1: the two-dimensional adjusting mechanism (10) is connected with the top of the universal portal frame;
step S2: after the laser tracker is adopted to precisely measure and adjust the rotating mechanism (20) to reach the required verticality, placing the theoretically calculated balance weight of the electronic scale under two steel wire ropes of the hanging beam;
step S3: after the initial resistance moment and the process resistance moment of the rotation of the test hanging beam meet the requirements, removing the balance weight of the electronic scale at the steel wire rope, and formally connecting the cabin door of the spacecraft in the closed state;
step S4: before the cabin door is connected, two adjusting screws below the hanging beam are adjusted to leave an equal length adjusting allowance, and the electronic scale on the steel wire rope is in a zero position;
step S5: precisely measuring and adjusting the perpendicularity of the cabin door damping speed stabilizing mechanism to reach a required value by adopting a laser tracker;
step S6: the coaxiality of the rotating mechanism (20), the cabin door hanging point and the damping speed stabilizing mechanism is ensured to meet the requirement of a precise measurement index through manual adjustment of the two-dimensional adjusting mechanism (10) and the cabin door hanging point;
step S7: the reading of the two electronic scales reaches the theoretical requirement value by adjusting the adjusting screws at the upper ends of the steel wire ropes at the two ends;
step S8: after the state is precisely measured and adjusted in place, zero gravity balance unfolding and folding under the drive of the cabin door driving mechanism of the spacecraft are realized.
2. The method for using the spacecraft cabin door zero gravity balance folding and unfolding test device according to claim 1, wherein the two-dimensional adjusting mechanism (10) performs two-dimensional manual adjustment in a plane through an X-direction manual adjusting device (11) and a Y-direction manual adjusting device (12).
3. The method for using the spacecraft cabin door zero gravity balance folding and unfolding test device according to claim 1, wherein the rotating mechanism (20) consists of an upper flange (21), a deep groove ball bearing (22), a first lining plate, a plane bearing (24), a second lining plate, a cylinder body (26), a bearing retainer ring (27), a lower flange (28) and a rotating shaft (29); the deep groove ball bearings (22) are positioned at two ends of the plane bearing (24).
4. Use of a spacecraft cabin door zero gravity balance deployment and retraction test device according to claim 1, characterized in that the lifting beam is rigidly connected to the swivel mechanism (20) by means of a flange.
5. The method for using the spacecraft cabin door zero gravity balance folding and unfolding test device according to claim 1, wherein the linear guide rail at the end part of the hanging beam automatically moves according to the stress direction of the steel wire rope below the hanging beam, and the steel wire rope is found and reaches the coaxiality of the steel wire rope and a cabin door hanging point.
6. A method for using a space vehicle cabin door zero gravity balance folding and unfolding test device according to claim 3, wherein the step S1 further comprises the step of connecting the rotating mechanism (20) with the hanging beam flange plate through the lower flange (28) and then integrally connecting the rotating mechanism (20) with the central flange surface of the bottom surface of the two-dimensional adjusting mechanism (10) through the upper flange (21) at the upper end of the rotating mechanism.
7. The method for using the spacecraft cabin door zero gravity balance folding and unfolding test device according to claim 1, wherein the step S2 further comprises the steps of adopting a precision chest expander to slowly and smoothly pull the hanging beam for one circle along the tangential direction of the rotation of the hanging beam at the fixed position of the steel wire rope at the end part of the hanging beam, and testing the initial resistance moment and the process resistance moment of the rotation of the hanging beam.
8. The method according to claim 1, wherein the step S4 further comprises connecting two steel wires to the hanging points at two ends of the cabin door, the steel wires at two ends are slightly tensioned by adjusting the screw, and the electronic scales are in the same reading.
9. The method according to claim 1, wherein the verticality of the steel wire rope connecting the door hanging point in the step S7 is automatically adjusted in place by the movement of the linear guide rail during the adjustment of the adjusting screw.
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| CN202111197723.1A CN113859592B (en) | 2021-10-14 | 2021-10-14 | Zero-gravity balance unfolding and folding test device for cabin door of spacecraft and application method |
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| CN202111197723.1A CN113859592B (en) | 2021-10-14 | 2021-10-14 | Zero-gravity balance unfolding and folding test device for cabin door of spacecraft and application method |
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| CN113859592B true CN113859592B (en) | 2024-02-09 |
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