CN108760267B - Microgravity test system of separating mechanism - Google Patents
Microgravity test system of separating mechanism Download PDFInfo
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- CN108760267B CN108760267B CN201810562527.1A CN201810562527A CN108760267B CN 108760267 B CN108760267 B CN 108760267B CN 201810562527 A CN201810562527 A CN 201810562527A CN 108760267 B CN108760267 B CN 108760267B
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- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
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Abstract
The application relates to a microgravity test system of a separating mechanism, which comprises a truss, the separating mechanism, a satellite, an equal weight block which is equal to the weight of the satellite, a rope which is connected with the satellite and the equal weight block, a laser measuring instrument and an angular velocity sensor.
Description
Technical Field
The invention relates to a test system, in particular to a microgravity test system of a satellite-rocket separation mechanism
Background
In the process of developing the separation mechanism, the performance of the separation mechanism needs to be examined, including impact on a satellite caused by unlocking, separation speed and separation angular speed after the satellite is released. Under the influence of gravity, the accuracy of the measured separation speed and angular speed is difficult to guarantee. The separation speed and angular velocity errors estimated by means of a high-speed camera are large.
At present, the separation test of the satellite and rocket separation mechanism comprises the following steps:
1. satellite hoisting, separating mechanism unlocking and falling
The method is characterized in that the satellite is hoisted by a rope and is not fixed, and the energy stored by the separating mechanism is converted into the kinetic energy of the satellite and the separating mechanism at the same time during separation. The separation state is not comparable to the actual situation, so the in-orbit satellite separation velocity and separation angular velocity cannot be measured.
2. The separation mechanism is fixedly arranged and the satellite falls
According to the method, the separation mechanism is arranged on the truss, and the satellite falls freely under the action of gravity. Target points previously attached to the satellite are photographed by using 4 high-speed cameras, and the separation speed and the separation angular speed of the satellite are analyzed. The separation speed varies constantly due to the influence of gravity. On the other hand, the high-speed camera does not directly measure, typically 1000 frames/s, the high-speed camera with the resolution of 1000x1000 measures the speed error by about 0.5m/s, and measures the angular speed error by about 2 degrees/s.
Therefore, the development of a novel microgravity test system which can realize more accurate measurement of the separation speed is urgently needed in the field.
Disclosure of Invention
The application aims to provide a novel microgravity test system for a separating mechanism.
In order to achieve the above object, the present application provides the following technical solutions.
In a first aspect, the present application provides a separation mechanism microgravity test system, wherein the system comprises a truss, a separation mechanism and a satellite, an equal weight that is equal in weight to the satellite, a cable connecting the satellite and the equal weight, and a laser gauge and an angular velocity sensor.
In one embodiment of the present application, a deviation angle of the separation mechanism from a mounting surface of the satellite after mounting to a gravity direction is less than 0.1 °.
In another embodiment of the application, the rope passes through a pulley at the top end of the truss, one end of the rope is connected with the constant weight block, and the other end of the rope passes through the separating mechanism to be connected with the satellite through a lifting ring at the top end of the satellite.
In another embodiment of the present application, at least two pulleys capable of fine adjustment of position are installed on the top end of the truss.
In another embodiment of the present application, the minimum vertical distance of the satellite from the laser vibrometer is longer than the minimum vertical distance of the isobaric block from the pulley by at least one laser vibrometer.
In another embodiment of the present application, a reflective film is attached to the bottom surface of the satellite.
In another embodiment of the present application, an angular velocity sensor is affixed to an end face of the satellite.
In another embodiment of the present application, the satellite has a plurality of impact sensors affixed to a surface of the satellite.
Compared with the prior art, the test system has the advantages that the test system can accurately measure the performance of the satellite-rocket separation mechanism, including the speed and the angular speed of satellite separation and the impact generated during separation and unlocking; and simultaneously, the satellite can be protected. The measuring range of the separation speed is 0 m/s-5 m/s, and the precision is 0.1 m/s; the measurement range of the separation angular velocity is 0 degree/s-180 degree/s, and the measurement precision is 0.5 degree/s.
Drawings
FIG. 1 is a schematic view of a separation mechanism microgravity test system of the present application.
FIG. 2 is a schematic view of the disconnect mechanism and the weighted star of the present application and the sensor thereon.
Detailed Description
The technical solution of the present application will be clearly and completely described below with reference to the accompanying drawings and the embodiments of the present application.
In the test system of the present application for assessing separation mechanisms, the satellites may be replaced with weighted satellites. The balance weight star and the satellite have the same weight, mass center position, inertia, installation interface and the like.
The test system mainly comprises a truss, a separating mechanism, a balance weight star, an equal weight block, a laser vibration meter, an angular velocity sensor and the like, and is shown in figure 1.
The truss is formed by welding or screwing aluminum alloy pipes and is similar to a stage truss. The outer truss envelope size can be adjusted to suit the application, and in one embodiment of the present application, is 2.9m x 2.8m x 0.4.4 m. The truss structure should be strong enough to be able to carry at least 1000kg of weight.
After the separating mechanism and the balance weight star are installed well, the separating mechanism and the balance weight star are installed on the side face of the truss in a combined mode, and sponge pads are arranged below the truss and on the side face of the truss in a supported mode. The deviation angle between the installation surface of the separating mechanism and the gravity direction is less than 0.1 degrees so as to reduce the influence of gravity on the separating angular speed.
In one embodiment of the present application, the weight star is about 1m from the underlying sponge pad. And a rope penetrates through the pulley at the top end of the truss, one end of the rope is connected with the equal-weight block, and the other end of the rope penetrates through the separating mechanism and is connected with the balance weight star through a hanging ring at the top end of the balance weight star. The rope tension action line passes through the counterweight star centroid, so that the counterweight star separation angular speed is not influenced. The position of the pulley above the balance weight star is adjusted to enable the rope to be vertical. The rope is a powerful bridle wire with the diameter of 3mm, the frictional resistance is small, and the strength is high.
The position of the pulley can be finely adjusted, so that the rope suspension point is consistent with the mass center of the balance weight star. The weight of the equal weight block is the same as that of the balance weight star, so that the gravity borne by the balance weight star (replacing the satellite) can be counteracted through the rope. The weight blocks are cuboid and can be formed by processing steel, and threaded hoisting ring interfaces are reserved for rope connection.
In one embodiment of the application, the separating mechanism is tightly connected with the balance weight star through an electromagnetic chuck. When the electromagnetic chuck is powered off, the balance weight star moves in an accelerated manner under the push of the spring. The spring pushes a certain stroke to separate from the counterweight star, and at the moment, the counterweight star simultaneously receives self gravity and rope tension, and resultant force is close to 0, so that the counterweight star moves at a constant speed. At this time, the weight blocks move upwards immediately and stop moving after contacting the pulley. In one embodiment of the present application, the constant weight blocks are 780mm from the pulley design distance. In actual conditions, the falling stroke of the balance weight star can be limited by adjusting the actual installation height of the separating mechanism, so that the collision between the balance weight star and the laser vibration meter is avoided. In order to avoid the downward movement of the counterweight star to collide with the laser vibration meter, the minimum vertical distance between the counterweight star and the laser vibration meter (namely the vertical distance between the bottom end of the counterweight star and the top end of the laser vibration meter) is required to be longer than the minimum vertical distance between the counterweight block and the pulley (namely the vertical distance between the top end of the counterweight block and the pulley) by at least one distance of the laser vibration meter. In one embodiment of the present application, the laser measuring instrument is about 200mm high.
The laser vibration meter is placed on the horizontal ground. The bottom surface of the balance weight star is adhered with a reflecting film which reflects laser emitted from the laser vibrometer. And the laser vibration meter measures the movement speed of the balance weight star according to the time difference between the laser emission and the laser reception. The laser vibration meter outputs voltage signals which are collected by the data collector. The test table is arranged outside the truss, and the data acquisition instrument is arranged on the test table. The laser vibration meter is connected with the data acquisition instrument through a cable. The data acquisition instrument can acquire the voltage signal and analyze the voltage signal into motion speed data through LMS Test Lab software.
In the system, the elastic potential energy stored in the separating mechanism is converted into the kinetic energy of the counterweight star and the upper counterweight block. Therefore, the expected separation speed on the track is obtained by converting the separation speed measured by the laser vibration meter. The theoretically measured separation speed is 0.707 times the on-track expected separation speed.
As shown in fig. 2, at least one angular velocity sensor is adhered to the end surface of the balance weight star, and the angular velocity sensor is connected to a data acquisition instrument to directly acquire the separation angular velocities in three directions. The three directions are three coordinate axis directions of the satellite coordinate system, namely the directions of the horizontal plane in the paper surface, the vertical plane in the paper surface and the direction vertical to the paper surface.
Meanwhile, impact sensors are pasted at a plurality of positions of the balance weight star and connected to a data acquisition instrument to directly acquire and measure impact generated by the actuating and unlocking of the initiating explosive device.
In one embodiment of the application, data of the data acquisition instrument is recorded and processed by LMS Test Lab software at the PC terminal.
In one embodiment of the present application, the test devices participating in the trial are as follows:
(1) impact sensor
The specific parameters of the impact sensor used in this test are as follows:
sensitivity: 0.5 mV/g; measuring range: 10000 g; frequency range: 3 to 10000 Hz.
(2) Laser vibration meter
The specific parameters of the laser vibrometer used in this test are as follows:
speed range: +/-10 m/s; minimum resolution: a 0.02 micron/sec/Hz bandwidth; and (3) analog voltage output: max +/-10V; frequency range: 0-2.5 MHz.
(3) Data acquisition equipment
The specific parameters of the data acquisition equipment used in the test are as follows:
sampling frequency: 204.8 KHz;
the sampling mode is as follows: continuously;
lowest frequency: 5 Hz;
the highest frequency: 10000 Hz;
measurement error: less than 15%.
The experimental procedure of this example is as follows:
first, environmental requirements
a. The illumination is not lower than 300 lx;
b. the temperature meets 20 +/-5 ℃;
c. the relative humidity is 30-60%;
d. the cleanliness is superior to 10 ten thousand grades;
e. the noise is not more than 60 dB;
note that:
(1) in the test process, if the measured data is found to be seriously abnormal or the data cannot be measured and the test cannot be carried out, the data acquisition system, the sensor and the cable are checked, and if the sensor and the cable have faults, the test is continued after the sensor and the cable are repaired;
(2) in the test, if the structure or other parts are seriously damaged and the test cannot be carried out, stopping the test, and restarting the test from the starting point of the test after the damaged part is repaired and inspected again to be qualified;
(3) and if other faults are not detected by the self fault of the test system and can not be repaired in a short time, stopping the test, and storing the data as a reference. After the fault is repaired, the test is restarted.
Second, test site requirements
a. The area of the test site is not less than 6mX10 m;
b. 2-3 tables with the height of about 1m, the width of 1m and the length of 1-3 m are required to be provided for placing test equipment in a test field;
c. 1 anti-static test table is required to be provided for the test field for the fire test;
third, requirement of acquisition system
1) In order to avoid frequency aliasing, the digitized analog signal is subjected to low-pass filtering in advance, the cut-off frequency of a low-pass filter is the upper limit analysis frequency, and the out-of-band attenuation rate of the low-pass filter is more than 60 dB;
2) in order to ensure the signal analysis precision, the sampling frequency is generally 5-10 times of the low-pass cut-off frequency and not lower than 4 times of the low-pass cut-off frequency;
3) the sampling frequency is not lower than 50K.
Four, description of impact data processing
1) The data segment to be processed comprises the whole impact process, and the signal starts from the background noise and ends at the background noise;
2) the upper limit analysis frequency of the impact signal of the interface is not less than 5kHz, and the lower limit analysis frequency is not more than 50 Hz;
3) the frequency step is analyzed 1/6 octaves.
Fifth, safety requirements
1) During satellite tests, necessary isolation measures are adopted to isolate a test area from a working area, and a safety warning range is drawn out, so that workers are prevented from being injured by electric shock, high-altitude falling objects and the like.
2) Before a tester tests a field, static electricity needs to be discharged through static electricity discharging operation;
3) safety protection measures need to be made on the test site, and shields are placed around the star bodies to prevent redundant materials from flying out to damage peripheral equipment and personnel when initiating explosive devices are detonated.
Sixthly, testing other related requirements
The relevant requirements of the test include quality management, field order, technical security, confidentiality, quality problem handling and negotiation.
a. All measurement and test equipment must be acceptable and within the useful life;
b. all workers in the test field must obey the command and follow the field command for unified scheduling;
c. if abnormal conditions and faults are found, the equipment and instruments to be tested should be reported immediately, and the equipment and instruments to be tested can be tested only after the equipment and instruments to be tested are maintained normally and inspected to be qualified;
d. after the camera shooting data of the tester is tested, the video content is provided to the satellite side through engraving;
e. and (4) carrying out on-site negotiation on the satellite side and the tester side to solve the problems of emergencies and quality possibly in the process of affairs and test.
The embodiments described above are intended to facilitate the understanding and appreciation of the application by those skilled in the art. It will be readily apparent to those skilled in the art that various modifications to these embodiments may be made, and the generic principles described herein may be applied to other embodiments without the use of the inventive faculty. Therefore, the present application is not limited to the embodiments herein, and those skilled in the art who have the benefit of this disclosure will appreciate that many modifications and variations are possible within the scope of the present application without departing from the scope and spirit of the present application.
Claims (7)
1. A separation mechanism microgravity test system is characterized by comprising a truss, a separation mechanism, a satellite, an equal weight which is equal to the satellite, a rope which connects the satellite and the equal weight, a laser measuring instrument and an angular velocity sensor, wherein the deviation angle of a mounting surface of the separation mechanism after being mounted with the satellite and the gravity direction is smaller than 0.1 degrees, the position of a pulley is finely adjusted to enable a rope suspension point to be consistent with the mass center of the satellite, the angular velocity sensor is configured to collect separation angular velocities in three coordinate axis directions of a satellite coordinate system, the separation mechanism is tightly connected with the satellite through an electromagnetic chuck, and the satellite is accelerated to move under the pushing of a spring after the electromagnetic chuck is powered off.
2. The microgravity test system of the separating mechanism as claimed in claim 1, wherein the rope passes through a pulley at the top end of the truss, one end of the rope is connected with the constant weight block, and the other end of the rope passes through the separating mechanism and is connected with the satellite through a lifting ring at the top end of the satellite.
3. The release mechanism microgravity test system of claim 2, wherein the cable is a 3mm diameter high force wire.
4. The microgravity test system of claim 1, wherein the top end of the truss is provided with at least two pulleys capable of fine adjustment of position.
5. The microgravity test system of claim 1, wherein the bottom surface of the satellite is adhered with a reflective film.
6. The microgravity test system of a separation mechanism of claim 1, wherein an angular velocity sensor is affixed to an end face of the satellite.
7. The separation mechanism microgravity test system of claim 1, wherein the satellite has a plurality of impact sensors affixed to a surface thereof.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011180637.5A CN112141372B (en) | 2018-06-04 | 2018-06-04 | Microgravity test method for satellite-rocket separation mechanism |
| CN201810562527.1A CN108760267B (en) | 2018-06-04 | 2018-06-04 | Microgravity test system of separating mechanism |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810562527.1A CN108760267B (en) | 2018-06-04 | 2018-06-04 | Microgravity test system of separating mechanism |
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| CN202011180637.5A Division CN112141372B (en) | 2018-06-04 | 2018-06-04 | Microgravity test method for satellite-rocket separation mechanism |
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| CN108760267B true 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 |
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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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| 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 |
| US6193187B1 (en) * | 1998-12-31 | 2001-02-27 | Harry Scott | Payload carry and launch system |
| 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 |
| CN103009337B (en) * | 2012-12-06 | 2014-12-03 | 上海裕达实业公司 | Side plate installing vehicle for omnidirectional fine-tuning satellite instrument |
| 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 |
| CN104691781B (en) * | 2015-01-13 | 2016-09-21 | 中国空间技术研究院 | A kind of space-based platform based on Open architecture |
| 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 |
| CN105539878B (en) * | 2015-12-03 | 2018-06-26 | 上海卫星工程研究所 | Towards the large-scale truss type vibration-isolating platform structure of a variety of payload |
| CN108001713B (en) * | 2017-11-20 | 2020-07-14 | 上海卫星装备研究所 | On-orbit separation ground test device and detection method for double-star combined spacecraft |
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| CN108760267A (en) | 2018-11-06 |
| CN112141372B (en) | 2022-03-25 |
| CN112141372A (en) | 2020-12-29 |
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