CN113859592A - Zero-gravity-balance unfolding and folding test device for spacecraft cabin door and use method - Google Patents
Zero-gravity-balance unfolding and folding test device for spacecraft cabin door and use method Download PDFInfo
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- CN113859592A CN113859592A CN202111197723.1A CN202111197723A CN113859592A CN 113859592 A CN113859592 A CN 113859592A CN 202111197723 A CN202111197723 A CN 202111197723A CN 113859592 A CN113859592 A CN 113859592A
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- 238000012360 testing method Methods 0.000 title claims abstract description 35
- 238000000034 method Methods 0.000 title claims abstract description 33
- 230000005484 gravity Effects 0.000 claims abstract description 27
- 230000007246 mechanism Effects 0.000 claims description 84
- 229910000831 Steel Inorganic materials 0.000 claims description 42
- 239000010959 steel Substances 0.000 claims description 42
- 230000008569 process Effects 0.000 claims description 11
- 238000013016 damping Methods 0.000 claims description 10
- 230000000087 stabilizing effect Effects 0.000 claims description 10
- 239000000725 suspension Substances 0.000 claims description 6
- 230000008602 contraction Effects 0.000 abstract description 10
- 238000005259 measurement Methods 0.000 description 4
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
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- 239000003638 chemical reducing agent Substances 0.000 description 1
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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 zero-gravity balance unfolding and folding test device for a spacecraft cabin door and a using method. The zero-gravity balance expansion and contraction device has the advantages of simple structural form, simplicity and convenience in operation, small rotation resistance, good gravity compensation effect and reliable balance state, ensures that the spacecraft cabin door can effectively realize zero-gravity balance expansion and contraction under the action of limited driving torque, and provides a new scheme for a ground zero-gravity balance expansion and contraction test of the spacecraft cabin door.
Description
Technical Field
The invention relates to the technical field of spacecraft, in particular to a zero-gravity balance expansion and contraction test device for a spacecraft cabin door and a using method.
Background
When the spacecraft works in the space orbit, the gravity environment of the spacecraft is greatly different from the earth surface, and the spacecraft is almost in a weightless state when in orbit, such as a near-earth orbit spacecraft. The method is characterized in that when some spacecraft are in orbit, the smooth in-orbit unfolding and folding of the spacecraft doors are ensured to be in place so as to provide a window for subsequent in-and-out cabin tests of astronauts and cargo loads, although the zero-gravity state of the orbit can compensate the resistance moment generated by the weight of the doors on unfolding and folding of the spacecraft doors, the reliability of a hinge mechanism for providing driving moment for unfolding and folding of the doors is undoubtedly a core factor for restricting whether the spacecraft doors can be successfully unfolded and folded in orbit.
Patent document No. 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 positioning and braking functions, and belongs to the technical field of space mechanisms. The unfolding and folding mechanism comprises a cabin door separation frame, 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 shaft system, a cabin door hinge and a mechanism connecting rod assembly. The mechanism driving shaft system comprises a stepping motor, a speed reducer, an absolute type goniometer, a goniometer fixing seat, a left bearing seat, a right bearing seat, a bearing seat mounting plate, a goniometer coupling, a motor connecting shaft, a supporting bearing and an adjusting ring. The mechanism connecting rod assembly comprises a special-shaped 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 of the spacecraft in the orbit, the reliability of an unfolding and folding driving mechanism of the cabin door of the spacecraft must be ensured firstly, so that the reliability of the driving mechanism (hinge) for driving the cabin door of the spacecraft to unfold and fold smoothly is fully verified in the ground development stage before the spacecraft is launched under the zero gravity state in the orbit. Therefore, a set of zero-gravity balance unfolding and folding test tool for the aircraft cabin door, which has the characteristics of simple structure, convenience in operation, full gravity compensation of the cabin door, small self resistance moment of the 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 the driving mechanism (hinge) in a zero-gravity state is fully verified, so that a new scheme is provided for the zero-gravity balance unfolding and folding test of the cabin door of the spacecraft.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a zero-gravity balance unfolding and folding test device for a spacecraft cabin door and a using method thereof.
The zero-gravity balance unfolding and folding test device for the cabin door of the spacecraft, provided by the invention, 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 a mounting screw;
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 rotating mechanism and the hanging beam are integrally 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, and the steel wire rope and the cabin door lifting point are coaxial.
The invention also provides a using method of the zero gravity balance unfolding and folding test device for the spacecraft door, wherein the method applies the zero gravity balance unfolding and folding test device for the spacecraft door, and comprises the following steps:
step S1: the two-dimensional adjusting mechanism is connected with the top of the universal portal frame;
step S2: after a laser tracker is adopted to precisely measure and adjust the rotating mechanism to reach the required verticality, the balance weights after theoretical calculation are placed below the steel wire ropes at two positions 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 counter weight at the steel wire rope, and formally connecting the cabin door of the spacecraft in a closed state;
step S4: in front of the connecting cabin door, two adjusting screws below the adjusting hanging beam leave 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 verticality of the cabin door damping speed stabilizing mechanism to a required value by adopting a laser tracker;
step S6: the two-dimensional adjusting mechanism and the cabin door hoisting point are manually adjusted;
step S7: the reading numbers of the two electronic scales reach theoretical required values by adjusting screws at the upper ends of the steel wire ropes at the two ends;
step S8: after the state is accurately measured and adjusted in place, the zero gravity balance unfolding and folding is performed under the hinge drive of the cabin door driving mechanism of the spacecraft.
Preferably, the step S1 further includes connecting the rotating mechanism with the hanging beam flange plate through the lower flange, and then integrally connecting the rotating mechanism with the central flange surface of the bottom surface of the two-dimensional adjusting mechanism through the upper end flange of the rotating mechanism.
Preferably, the step S2 further includes using a precision tension device to slowly and smoothly pull the hanging beam by one turn in a tangential direction of the rotation of the hanging beam at the fixing position of the steel wire rope at the end 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 cables to the hanging points at the two ends of the door respectively, and slightly tightening the steel cables at the two ends by adjusting the screw rods, and the electronic scales are at the same reading.
Preferably, the perpendicularity of the wire rope connecting the door hanging points in the adjusting process of the adjusting screws in the step S7 is automatically adjusted to be 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 zero-gravity balance unfolding and folding test device for a cabin door of a spacecraft and a using method thereof, wherein a tool has the characteristics of simple structural form, convenience in operation, full gravity compensation on the cabin door, small self resistance moment and the like;
2. the invention can effectively realize the zero gravity balance state of the aircraft door, and fully verify the reliability of the hinge driving of the aircraft door by the driving mechanism in the zero gravity state;
3. the invention provides a new scheme for the zero gravity balance expansion and contraction test of the spacecraft cabin door.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic view of a spacecraft door of the present invention deployed to a 90 position at zero gravity;
FIG. 2 is a schematic view of the zero gravity deploying and retracting tool for the spacecraft door of the present invention;
fig. 3 is a schematic view of a zero-gravity unfolding and folding tool rotating mechanism of a spacecraft door of the invention.
Wherein:
first lining board 23 of two-dimensional adjusting mechanism 10
X-direction manual adjusting device 11 plane bearing 24
Second lining plate 25 of Y-direction manual adjusting device 12
Upper flange 21 bearing retainer 27
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 invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
The invention provides a zero-gravity balance unfolding and folding test device for a spacecraft cabin door and a using method, 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 a general portal frame, the rotating mechanism 20 is connected with a hanging beam flange plate through the lower flange 28, then the whole body is connected with the central flange surface of the bottom surface of the two-dimensional adjusting mechanism 10 through the upper end flange of the rotating mechanism 20, and the laser tracker is adopted to accurately measure and adjust the verticality of the rotating mechanism 20 to reach the requirement; and then installing a linear guide rail, an adjusting screw and a steel wire rope below the end part of the hanging beam, loading a balance weight which is calculated theoretically below the two steel wire ropes, adopting a precise tensioner at the fixed part of the steel wire rope at the end part of the hanging beam, slowly and smoothly pulling the hanging beam for a circle along the tangential direction of the rotation of the hanging beam, unloading the balance weight at the steel wire rope after testing that the initial resistance moment and the process resistance moment of the rotation of the hanging beam meet the requirements, and formally connecting the cabin door of the spacecraft in a closed state.
Before the cabin door is connected, two adjusting screws below the hanging beam are adjusted to reserve equal-length adjusting allowance, the electronic scales on the steel wire ropes are all in zero positions, then the two steel wire ropes are respectively connected with hanging points at two ends of the cabin door, the steel wire ropes at two ends are slightly tensioned through adjusting screw rods, 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 verticality is adjusted by three jacks below the cabin body, the coaxiality of the rotating mechanism 20, the cabin door lifting point and the damping speed stabilizing mechanism is guaranteed to meet the requirement of a precision measurement index through manual adjustment of the two-dimensional adjusting mechanism 10 and the cabin door lifting point, finally, the reading of two electronic scales reaches a theoretical requirement value through adjustment of adjusting screws at the upper ends of steel wire ropes at two ends, and the verticality of the steel wire rope connected with the cabin door lifting point is automatically adjusted in place through movement of the linear guide rail in the adjusting screw process. After the accurate measurement and adjustment of the state are in place, zero gravity balance expansion and contraction of the spacecraft cabin door under the driving 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, can effectively realize the coaxiality of the rotating mechanism 20, a cabin door lifting point and a damping speed stabilizing mechanism, and avoids the coaxiality deviation from generating resistance moment for expansion and contraction of the cabin door.
The rotating mechanism 20 is composed 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 for the rotating shaft 29, and the structural layout of the two deep groove ball bearings 22 at the two ends of the plane bearing 24 not only effectively avoids the deflection deformation of the rotating shaft 29 when the rotating shaft is subjected to unbalance loading, but also enables the rotating mechanism 20 to 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 still has certain unbalance loading under the state of being connected with the cabin door and applying theoretical balance weight, thereby avoiding the resistance moment of the cabin door expansion and contraction caused by the bending of the hanging beam.
The linear guide rail at the end part of the hanging beam can automatically move according to the stress direction of the steel wire rope below the linear guide rail, and reliably finds and reaches the coaxiality of the steel wire rope and the cabin door hanging point, thereby effectively avoiding the increase of the resisting moment of the expansion and contraction of the cabin door caused by the torque generated by the inclined hanging force of the steel wire rope on the damping speed stabilizing mechanism.
The use of adjusting screw and electronic scale can be effectively adjusting the taut length of wire rope in-process, reliably guarantees the balanced of suspension system to hatch door theoretical gravity through the monitoring of electronic scale registration to avoid the unable balanced hatch door gravity of wire rope tension and lead to the increase of the moment of resistance of hatch door exhibition receipts.
A use method of a zero-gravity balance unfolding and folding test device for a spacecraft cabin door 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 end flange of the rotating mechanism 20.
Step S2: after the laser tracker is adopted to accurately measure and adjust the rotating mechanism 20 to reach the required verticality, the balance weights after theoretical calculation are placed below the steel wire ropes at two positions of the hanging beam, the hanging beam is slowly and smoothly pulled for a 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 by adopting a precise tension device, 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 of the rotation of the test hanging beam meet the requirements, removing the counter weight at the steel wire rope, and formally connecting the cabin door of the spacecraft in a closed state.
Step S4: before the cabin door is connected, two adjusting screws below the hanging beam are adjusted to reserve equal-length adjusting allowance, the electronic scales on the steel wire ropes are all in zero positions, then the two steel wire ropes are respectively connected with hanging points at two ends of the cabin door, the steel wire ropes at two ends are slightly tensioned through adjusting screw rods, and the electronic scales are in the same reading.
Step S5: and precisely measuring and adjusting the verticality of the cabin door damping speed stabilizing mechanism by adopting a laser tracker to reach a required value.
Step S6: through the manual adjustment of the two-dimensional adjusting mechanism 10 and the cabin door hoisting point, the coaxiality of the rotating mechanism 20, the cabin door hoisting point and the damping speed stabilizing mechanism is ensured to meet the requirement of a precision measurement index.
Step S7: the reading numbers of the two electronic scales reach theoretical required values by adjusting the adjusting screws at the upper ends of the steel wire ropes at the two ends, and the perpendicularity of the steel wire ropes connected with the cabin door hoisting points can be automatically adjusted in place by moving the linear guide rails in the adjusting screw process.
Step S8: after the accurate measurement and adjustment of the state are in place, zero-gravity balance unfolding and folding under the hinge drive of the cabin door driving mechanism of the spacecraft can be realized.
The invention provides a zero-gravity balance unfolding and folding test device for a cabin door of a spacecraft and a using method thereof, wherein a tool has the characteristics of simple structural form, convenience in operation, full gravity compensation on the cabin door, small self resistance moment and the like; the zero gravity balance state of the aircraft door can be effectively realized, and the reliability of the driving mechanism hinge driving the aircraft door to unfold and fold in the zero gravity state is fully verified; provides a new scheme for the zero gravity balance expansion and contraction test of the spacecraft door.
Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, units provided by the present invention as pure computer readable program code, the system and its various devices, modules, units provided by the present invention can be fully implemented by logically programming method steps in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. 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 included in the system for realizing various functions can also be regarded as structures in the hardware component; means, modules, units for performing the various functions may also be regarded as structures within both software modules and hardware components for performing the method.
In the description of the present application, it is to 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 those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A zero gravity balance unfolding and folding test device for a spacecraft cabin door 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 a mounting 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 rotating mechanism (20) and the hanging beam are integrally connected with the two-dimensional adjusting mechanism (10); and a linear guide rail, an adjusting screw and a steel wire rope are arranged below the end part of the hanging beam.
2. The spacecraft door zero-gravity balance deployment test apparatus of claim 1, wherein the two-dimensional adjustment mechanism (10) performs two-dimensional manual adjustment in a plane by means of an X-direction manual adjustment device (11) and a Y-direction manual adjustment device (12).
3. The spacecraft door zero-gravity balance deployment test device of claim 1, wherein the rotating mechanism (20) is composed of an upper flange (21), a deep groove ball bearing (22), a lining plate, a plane bearing (24), a lining plate, a cylinder (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. The spacecraft door zero gravity balance deployment test apparatus of claim 1, wherein the suspension beam and the rotation mechanism (20) are rigidly connected by a flange.
5. The spacecraft door zero-gravity balance unfolding and folding test device according to claim 1, wherein the linear guide rail at the end 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 same axis with the door lifting point.
6. Method of use of a spacecraft door zero gravity balance spread test apparatus, characterized in that the method applies a spacecraft door zero gravity balance spread test apparatus according to any of claims 1-5, the method comprising the steps of:
step S1: the two-dimensional adjusting mechanism (10) is connected with the top of the universal portal frame;
step S2: after the verticality of the rotating mechanism (20) is accurately measured and adjusted by adopting a laser tracker to meet the requirement, the balance weights after theoretical calculation are placed below the steel wire ropes at two positions 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 counter weight at the steel wire rope, and formally connecting the cabin door of the spacecraft in a closed state;
step S4: in front of the connecting cabin door, two adjusting screws below the adjusting hanging beam leave 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 verticality of the cabin door damping speed stabilizing mechanism to a required value by adopting a laser tracker;
step S6: the two-dimensional adjusting mechanism (10) and the cabin door hoisting point are manually adjusted;
step S7: the reading numbers of the two electronic scales reach theoretical required values by adjusting screws at the upper ends of the steel wire ropes at the two ends;
step S8: after the state is accurately measured and adjusted in place, the zero gravity balance unfolding and folding is performed under the hinge drive of the cabin door driving mechanism of the spacecraft.
7. The use method of the zero gravity balance unfolding and folding test device for spacecraft doors according to claim 6, wherein the step S1 further comprises 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 end flange of the rotating mechanism (20).
8. The use method of the spacecraft door zero-gravity-balance spread-and-retract test apparatus of claim 6, wherein the step S2 further comprises using a precision tensioner to slowly and smoothly pull the suspension beam for one turn at the cable fixing position at the end of the suspension beam in a tangential direction of the rotation of the suspension beam, and testing the initial resistance moment and the process resistance moment of the rotation of the suspension beam.
9. The use method of the spacecraft door zero-gravity balance unfolding and folding test device according to claim 6, wherein the step S4 further comprises connecting two steel cables with hanging points at two ends of the door respectively, slightly tensioning the steel cables at two ends by adjusting screws, and keeping the electronic scales at the same reading.
10. The use method of the zero gravity balance unfolding and folding test device for a spacecraft door of claim 6, wherein the perpendicularity of the wire rope connecting the door hanging points in the step S7 is automatically adjusted to be in place by moving the linear guide rail in the process of adjusting the adjusting screws.
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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 CN113859592B (en) | 2024-02-09 |
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2021
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