CN108760267A - Separating mechanism microgravity test system - Google Patents
Separating mechanism microgravity test system Download PDFInfo
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- CN108760267A CN108760267A CN201810562527.1A CN201810562527A CN108760267A CN 108760267 A CN108760267 A CN 108760267A CN 201810562527 A CN201810562527 A CN 201810562527A CN 108760267 A CN108760267 A CN 108760267A
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- separating mechanism
- satellite
- test system
- microgravity test
- microgravity
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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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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Balance (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
This application involves a kind of separating mechanism microgravity test systems, the system comprises a truss, a separating mechanism and satellite, and the equal pouring weights of the weight such as one and satellite, the rope and laser measuring apparatus and angular-rate sensor of connection satellite and grade pouring weights.
Description
Technical field
It is to be related to a kind of pilot system this application involves the present invention, is tried more particularly to a kind of satellite and the rocket separating mechanism microgravity
Check system
Background technology
It in separating mechanism development process, needs to examine the performance of separating mechanism, including unlock generates satellite
Impact, the separating rate after satellite release and separation angular speed.Under the influence of gravity, the separating rate of measurement, angular speed are difficult
To ensure accuracy.The separating rate and angular speed error calculated by means of high-speed camera is larger.
The separation test of satellite and the rocket separating mechanism has at present：
1. satellite is sling, separating mechanism unlock is fallen
This method passing of satelline rope is sling, and is not fixed, and the energy of separating mechanism storage is converted into satellite simultaneously when separation
With the kinetic energy of separating mechanism.Discrete state does not have comparativity with actual conditions, so in-orbit satellite separating rate and the angle of departure
Speed is unable to measure acquisition.
2. separating mechanism installation is fixed, satellite falls
Separating mechanism is installed on truss by this method, satellite free-falling under the effect of gravity.Use 4 high-speed cameras
Machine shooting is pasted on the target point on satellite in advance, to parse the separating rate and separation angular speed of satellite.Due to gravity
Influence, separating rate changes always.On the other hand, high-speed camera indirectly measurement, typical such as 1000 frames/s,
1000x1000 resolution ratio high-speed camera measuring speed errors 0.5m/s or so measures 2 °/s of angular speed error or so.
For this purpose, there is an urgent need in the art to develop a kind of novel microgravity test system, it can realize that separating rate is more acurrate
Measurement.
Invention content
The application's is designed to provide a kind of novel separating mechanism microgravity test system.
To achieve the goals above, the application provides following technical proposals.
In the first aspect, the application provides a kind of separating mechanism microgravity test system, wherein the system comprises one
Truss, a separating mechanism and satellite, the equal pouring weights of the weight such as one and satellite, the rope and Laser Measuring of connection satellite and grade pouring weights
Measure instrument and angular-rate sensor.
In a kind of embodiment of the application, mounting surface and gravity direction after the installation of the separating mechanism and satellite
The angle of deviation is less than 0.1 °.
In the another embodiment of the application, the rope pass through the truss top pulley, one end with it is described
Equal pouring weights are connected, and the other end passes through separating mechanism to connect satellite by the hanging ring on satellite top.
In the another embodiment of the application, the truss top be equipped with it is at least two can be with trim locations
Pulley.
In the another embodiment of the application, the pouring weights such as minimum perpendicular distance ratio of the satellite and laser vibration measurer
It is grown at a distance from least one laser vibration measurer with the minimum perpendicular distance of pulley.
In the another embodiment of the application, the bottom surface of the satellite is pasted with reflectance coating.
In the another embodiment of the application, the end face of the satellite is pasted with angular-rate sensor.
In the another embodiment of the application, the surface mount of the satellite has multiple shock transducers.
Compared with prior art, the advantageous effect of the application is that this pilot system can accurately measure satellite and the rocket separating mechanism
Performance, including the speed of satellite separation, angular speed, the impact that separation generates when unlocking；Satellite can be protected simultaneously.Its
Separating rate measurement range is 0m/s~5m/s, precision 0.1m/s；Angular velocity measurement ranging from 0 °/s~180 °/s is detached, is measured
0.5 °/s of precision.
Description of the drawings
Fig. 1 is the schematic diagram of the separating mechanism microgravity test system of the application.
Fig. 2 is the separating mechanism and counterweight star and the schematic diagram of sensor thereon of the application.
Specific implementation mode
Below in conjunction with attached drawing and embodiments herein, carries out clear to the technical solution of the application and completely retouch
It states.
For examining in the pilot system of the application of separating mechanism, satellite can use counterweight star to substitute.Counterweight star with defend
Star has identical weight, centroid position, inertia and installation interface etc..
This pilot system includes mainly a truss, and separating mechanism, counterweight star waits pouring weights, laser vibration measurer and angular speed
Sensor etc., as shown in Figure 1.
The truss is welded or is spirally connected by aluminium-alloy pipe, is similar to stage truss.Truss external envelope size can basis
Actual conditions are adjusted, and in one embodiment of the application, size is 2.9m x 2.8m x 0.4m.Truss structure is answered
It is sufficiently solid, it should be able at least carry the weight of 1000kg.
After separating mechanism is installed with counterweight star, a combination thereof is installed on truss side, and foam-rubber cushion is padded in truss lower section and side.
The angle of deviation of separating mechanism mounting surface and gravity direction should be less than 0.1 °, to reduce influence of the gravity to separation angular speed.
In one embodiment of the application, foam-rubber cushion about 1m of the counterweight star apart from lower section.Separately there is a rope to wear
The pulley on the truss top is crossed, one end is connected with equal pouring weights, and the other end passes through hanging ring of the separating mechanism by counterweight star top
Connect counterweight star.Rope pull position is by counterweight star barycenter, to not had an impact to counterweight star separation angular speed.It adjusts
Pulley position above counterweight star keeps rope vertical.Rope selects diameter 3mm horse lines energetically, and frictional resistance is small, and intensity is high.
Pulley position is fine-tuning, to ensure that rope hanging point is consistent with counterweight star barycenter.Equal pouring weights weight and counterweight star
It is identical, so as to offset the gravity that counterweight star is born (instead of satellite) by rope.Equal pouring weights are in cuboid, can be processed by steel
It forms, there are screw thread hanging ring interfaces to connect for rope.
In one embodiment of the application, connection is sucked by magnechuck between the separating mechanism and counterweight star.
After being powered off to magnechuck, counterweight star accelerates under spring promotion.Spring is detached from after pushing certain stroke with counterweight star,
At this point, counterweight star is close to 0 with joint efforts simultaneously by its own gravity and rope pull, to constant speed movement.At this point, waiting
Pouring weight moves upwards immediately, contacts stop motion after pulley.In one embodiment of the application, wait pouring weights away from roller design away from
From 780mm.It can be adjusted according to separating mechanism actual installation height in actual conditions, need to guarantee to limit counterweight star whereabouts
Stroke, to avoid counterweight star from being collided with laser vibration measurer.Laser vibration measurer is bumped against in order to avoid counterweight star moves downward, it is desirable that
The minimum perpendicular distance (i.e. the vertical range of counterweight star bottom end and laser vibration measurer top) of counterweight star and laser vibration measurer ratio etc.
Minimum perpendicular distance (vertical range on i.e. equal pouring weights top and pulley) long at least one laser vibration measurer of pouring weight and pulley
Distance.In one embodiment of the application, the high about 200mm of the laser measuring apparatus.
Laser vibration measurer is positioned on level ground.Counterweight star bottom surface is pasted with reflectance coating, reflects from laser vibration measurer
Laser.Laser vibration measurer is according to the movement velocity of the time difference measurements counterweight star for sending out and receiving laser.Laser vibration measurer is defeated
Go out voltage signal, is acquired by data collecting instrument.Test desk is arranged outside truss, and data collecting instrument is placed on test desk.Vibration measurement with laser
Instrument connects data collecting instrument by cable.Voltage signal acquisition can be passed through LMS Test Lab softwares by data collecting instrument
It is parsed into angular movement speed data.
In such a system, since the elastic potential energy of separating mechanism internal reservoir is converted into counterweight star plus the dynamic of equal pouring weights
Energy.Therefore separating rate should be measured to laser vibration measurer and is converted to obtain in-orbit expected separating rate.Theoretically survey separation speed
Degree is 0.707 times of in-orbit expected separating rate.
As shown in Fig. 2, at least one angular-rate sensor is pasted on the end face of the counterweight star, and the angular speed passes
Sensor is connected to data collecting instrument, directly acquires three directions and detaches angular speed.Three directions are three, co-ordinates of satellite systems
Change in coordinate axis direction, i.e., it is horizontal in paper, it is vertical in paper, and perpendicular to paper direction.
Meanwhile shock transducer is pasted in multiple positions of counterweight star, and the shock transducer is connected to data acquisition
Instrument directly acquires and measures the impact that priming system start unlock generates.
In one embodiment of the application, data collecting instrument data kept a record by the ends PC LMS Test Lab softwares and
Reason.
In one embodiment of the application, the test equipment for participating in experiment is as follows：
(1) shock transducer
The design parameter of shock transducer used in this experiment is as follows：
Sensitivity：0.5mV/g；Range：10000g；Frequency range：3~10000Hz.
(2) laser vibration measurer
The design parameter of laser vibration measurer used in this experiment is as follows：
Speed range：+/-10m/s；Minimum resolution：0.02 micro- meter per second/Hz bandwidth；Analog voltage exports：It is maximum +/-
10V；Frequency range：0—2.5MHz.
(3) data acquisition equipment
The design parameter of data acquisition equipment used in this experiment is as follows：
Sample frequency：204.8KHz；
Sample mode：Continuously；
Low-limit frequency：5Hz；
Highest frequency：10000Hz；
Measurement error：Less than 15%.
The experiment process of the present embodiment is as follows：
One, environmental requirement
A. illuminance is not less than 300lx；
B. temperature meets 20 DEG C ± 5 DEG C；
C. relative humidity is 30%~60%；
D. cleanliness factor is better than 100,000 grades；
E. noise is not more than 60dB；
Points for attention：
(1) during testing, find measurement data severely subnormal, or can not data measured, experiment can not carry out, then answer
Data actuation, sensor and cable are checked, if there are failures for sensor and its cable, then are further continued for testing after repairing；
(2) in testing, it is found that structure or other component well damage, experiment can not carry out, then stop testing, wait for damage portion
It point repairs and again after the assay was approved, experiment is tested starting point from this and restarted；
(3) if other failures stop experiment, and preserve encounter non-test system failure itself and can not repair in short-term
Data are as reference.After fault restoration, this experiment restarts.
Two, test site requires
A. test site area is not less than 6mX10m；
B. test site need to provide 2~3 about 1m high, 1m wide, 1~3m long tables for putting test equipment；
C. test site need to provide 1 antistatic test desk, be tested for firer；
Three, acquisition system requirement
1) it is to avoid frequency alias, the analog signal being digitized should first pass through low-pass filtering in advance, and low-pass filter is cut
Only frequency is Upper bound analysis frequency, and low-pass filter attenuation outside a channel rate is more than 60dB；
2) it is to ensure that signal analysis precision, sample frequency are generally 5~10 times of low-pass cut-off frequencies, is cut not less than low pass
Only 4 times of frequency；
3) sample frequency is not less than 50K.
Four, data processing spec is impacted
1) data segment handled includes impact overall process, and signal originates in background noise, terminates at background noise；
2) 5kHz is not less than to the impact signal Upper bound analysis frequency of interface, the frequency of lower bound analysis is not more than 50Hz；
3) 1/6 octave of frequency step is analyzed.
Five, security requirement
1) it when Satellite Experiment, takes necessary quarantine measures that trial zone is isolated with workspace, marks Security alert range,
It is shocked by electricity to avoid staff, the injury of high falling object etc..
2) before testing crew test site, electrostatic need to be discharged by electrostatic discharge operation；
3) testing ground need to carry out safety prevention measure, and it is extra when screen prevents priming system from detonating to be placed around celestial body
Object flies out generates injury to peripheral equipment and personnel.
Six, other related requests are tested
In terms of the related request of experiment includes quality management, live order, skill peace, secrecy, quality matter and negotiation.
A. all measurements and testing equipment must be qualified and in the period of use；
B. testing ground all staff on board must obey commander, accept floor manager United Dispatching；
C. participate in the experiment equipment, instrument such as notes abnormalities and should be reported immediately with failure, and Awaiting Overhaul is normal and through after the assay was approved
It can participate in the experiment；
D. video content dish is provided to satellite side after the experiment of experiment side's camera shooting data；
E. it uses up in matters and experiment and is likely to occur accident, quality problems, satellite side, experiment side scene are resolved through consultation.
The above-mentioned description to embodiment is that this Shen can be understood and applied for the ease of those skilled in the art
Please.Person skilled in the art obviously easily can make various modifications to these embodiments, and described herein
General Principle is applied in other embodiments without paying performing creative labour.Therefore, the application is not limited to implementation here
Example, those skilled in the art make according to herein disclosed content in the case where not departing from the application scope and spirit
It improves and changes within all scope of the present application.
Claims (9)
1. a kind of separating mechanism microgravity test system, which is characterized in that the system comprises a truss, a separating mechanism and defend
Star, the equal pouring weights of the weight such as one and satellite, the rope and laser measuring apparatus and angular-rate sensor of connection satellite and grade pouring weights.
2. separating mechanism microgravity test system as described in claim 1, which is characterized in that the separating mechanism is pacified with satellite
The angle of deviation of mounting surface and gravity direction after dress is less than 0.1 °.
3. separating mechanism microgravity test system as described in claim 1, which is characterized in that the rope passes through the truss
The pulley on top, one end are connected with the equal pouring weights, and the other end passes through separating mechanism to connect satellite by the hanging ring on satellite top.
4. separating mechanism microgravity test system as claimed in claim 3, which is characterized in that the rope selects diameter 3mm
Horse line energetically.
5. separating mechanism microgravity test system as described in claim 1, which is characterized in that the truss top be equipped with to
Few two or more can be with the pulley of trim locations.
6. separating mechanism microgravity test system as described in claim 1, which is characterized in that the satellite and laser vibration measurer
Minimum perpendicular distance at least one laser vibration measurer longer than the minimum perpendicular distance of equal pouring weights and pulley at a distance from.
7. separating mechanism microgravity test system as described in claim 1, which is characterized in that the bottom surface of the satellite is pasted with
Reflectance coating.
8. separating mechanism microgravity test system as described in claim 1, which is characterized in that the end face of the satellite is pasted with
Angular-rate sensor.
9. separating mechanism microgravity test system as described in claim 1, which is characterized in that the surface mount of the satellite has
Multiple shock transducers.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810562527.1A CN108760267B (en) | 2018-06-04 | 2018-06-04 | Microgravity test system of separating mechanism |
| CN202011180637.5A CN112141372B (en) | 2018-06-04 | 2018-06-04 | Microgravity test method for satellite-rocket separation mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810562527.1A CN108760267B (en) | 2018-06-04 | 2018-06-04 | Microgravity test system of separating mechanism |
Related Child Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011180637.5A Division CN112141372B (en) | 2018-06-04 | 2018-06-04 | Microgravity test method for satellite-rocket separation mechanism |
Publications (2)
| Publication Number | Publication Date |
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| CN108760267A true CN108760267A (en) | 2018-11-06 |
| CN108760267B CN108760267B (en) | 2020-11-24 |
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|---|---|---|---|
| CN202011180637.5A Active CN112141372B (en) | 2018-06-04 | 2018-06-04 | Microgravity test method for satellite-rocket separation mechanism |
| CN201810562527.1A Active CN108760267B (en) | 2018-06-04 | 2018-06-04 | Microgravity test system of separating mechanism |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011180637.5A Active CN112141372B (en) | 2018-06-04 | 2018-06-04 | Microgravity test method for satellite-rocket separation mechanism |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114194424B (en) * | 2021-12-10 | 2023-10-31 | 清华大学 | Satellite gripper gravity unloading device and application method thereof |
| CN116513508B (en) * | 2023-04-04 | 2024-04-09 | 北京航空航天大学 | Gravity unloading experiment platform for space docking mechanism and application method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6193187B1 (en) * | 1998-12-31 | 2001-02-27 | Harry Scott | Payload carry and launch system |
| CN103009337A (en) * | 2012-12-06 | 2013-04-03 | 上海裕达实业公司 | Side plate installing vehicle for omnidirectional fine-tuning satellite instrument |
| CN104691781A (en) * | 2015-01-13 | 2015-06-10 | 中国空间技术研究院 | Space-based platform based on open structure |
| CN105539878A (en) * | 2015-12-03 | 2016-05-04 | 上海卫星工程研究所 | Large truss type vibration isolation platform structure facing various effective loads |
| CN108001713A (en) * | 2017-11-20 | 2018-05-08 | 上海卫星装备研究所 | Double star assembly spacecraft is in-orbit discretely to interview experiment device and detection method |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3044934B2 (en) * | 1992-07-06 | 2000-05-22 | 石川島播磨重工業株式会社 | Separation method of drop-type zero-gravity experimental device |
| CN102923318B (en) * | 2012-11-26 | 2015-05-27 | 上海宇航系统工程研究所 | Weak impact type butting system for androgynous stiffness damping closed loop feedback control |
| CN108811524B (en) * | 2013-07-12 | 2016-01-27 | 上海宇航系统工程研究所 | The system of satellite separation test under stimulated microgravity |
| CN106275491B (en) * | 2015-05-29 | 2018-07-20 | 北京卫星环境工程研究所 | Large Spacecraft Ground zero-gravity separation test is equipped |
-
2018
- 2018-06-04 CN CN202011180637.5A patent/CN112141372B/en active Active
- 2018-06-04 CN CN201810562527.1A patent/CN108760267B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6193187B1 (en) * | 1998-12-31 | 2001-02-27 | Harry Scott | Payload carry and launch system |
| CN103009337A (en) * | 2012-12-06 | 2013-04-03 | 上海裕达实业公司 | Side plate installing vehicle for omnidirectional fine-tuning satellite instrument |
| CN104691781A (en) * | 2015-01-13 | 2015-06-10 | 中国空间技术研究院 | Space-based platform based on open structure |
| CN105539878A (en) * | 2015-12-03 | 2016-05-04 | 上海卫星工程研究所 | Large truss type vibration isolation platform structure facing various effective loads |
| CN108001713A (en) * | 2017-11-20 | 2018-05-08 | 上海卫星装备研究所 | Double star assembly spacecraft is in-orbit discretely to interview experiment device and detection method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112141372B (en) | 2022-03-25 |
| CN108760267B (en) | 2020-11-24 |
| CN112141372A (en) | 2020-12-29 |
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