CN203949788U - The device that a kind of satellite or rocket Upper Stage propulsion subsystem barycenter are measured and weighed - Google Patents
The device that a kind of satellite or rocket Upper Stage propulsion subsystem barycenter are measured and weighed Download PDFInfo
- Publication number
- CN203949788U CN203949788U CN201420028573.0U CN201420028573U CN203949788U CN 203949788 U CN203949788 U CN 203949788U CN 201420028573 U CN201420028573 U CN 201420028573U CN 203949788 U CN203949788 U CN 203949788U
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- China
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- propulsion subsystem
- adapter ring
- weighing module
- top board
- upper stage
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Abstract
The utility model discloses the device that a kind of satellite or rocket Upper Stage propulsion subsystem barycenter are measured and weighed, this device by: base plate, joist steel, top board, Weighing module, thermal insulation board, adapter ring form.Wherein Weighing module consists of the stop means on top board, top board, base plate, 0745 stainless steel welded seal LOAD CELLS, sensor connecting piece.Weighing module prolongs adapter ring radial arrangement, and 4 tunnel modules are uniform by 90 degree.Upper Stage propulsion subsystem base docks with bolt with adapter ring, is vertically mounted on adapter ring, carries out ground level heat test run.By 4 road Weighing modules, bear the centroid position that heavy component of force calculates propulsion subsystem, measure after different test programs the variation of propulsion subsystem centroid position.By measuring propulsion subsystem total weight, go out the amount of releasing of propellant after the real-time consumption of propellant in repropellenting amount before test run and test run and test run simultaneously.
Description
Technical field
The present invention relates to the device that a kind of satellite or rocket Upper Stage propulsion subsystem barycenter are measured and weighed, relate in particular to the barycenter measurement of a kind of satellite or rocket Upper Stage propulsion subsystem ground run special use and the system of weighing, belong to test and use measurement mechanism field.
Background technology
Satellite or the heat run of rocket Upper Stage propulsion subsystem, the reliability of main examination Propulsion Subsystem Structure, the environmental suitability of parts and the matching of various parts, in the ground firing of the whole star system of general arrangement of first sample development stage, under atmospheric conditions, verify that propulsion subsystem requires the ability of normal work according to program.Wherein Residual Propellant test, filling flow verification, during primary engine operation, tank balance in parallel is discharged the aspects such as matching and need to be used the measurement of propulsion subsystem barycenter and weighing device.Owing to carrying out, satellite or rocket Upper Stage propulsion subsystem heat run cost are higher, in propulsion subsystem repropellenting process, adding amount measuring accuracy are required high, need accurately to measure the adding amount of single oxygenant fuel tank.After difference firer condition, there is certain deviation in the whole barycenter of propulsion subsystem, by multiple spot, weighed and surveyed barycenter method, can obtain the position of propulsion subsystem barycenter.
This barycenter is measured and weighing device is applied in satellite or rocket Upper Stage propulsion subsystem engine ignition process, can measure real-time propellant waste, can measure barycenter again.In engine ignition process, Weighing module also will be subject to thermal-radiating impact.This device has been made thermal insulation board specially, thereby the impact of the radiation heat that minimizing propulsion subsystem main engine ignition produces on sensor is a kind of new device that is applied in satellite or the test of rocket Upper Stage propulsion subsystem.
Summary of the invention
The device that satellite or rocket Upper Stage propulsion subsystem barycenter are measured and weighed, comprising: base plate, joist steel, top board, Weighing module, thermal insulation board, adapter ring form.Wherein Weighing module consists of the stop means on top board, top board, base plate, 0745 stainless steel welded seal LOAD CELLS, sensor connecting piece.
Base plate annulus is welded on two layers of test cell strengthening steel slab, has the circular hole for Upper Stage propulsion subsystem main engine ignition on steel plate.Joist steel and top board weld, and adopt joist steel can make propellant fill-drain lines road, distribution pipeline and measurement and control cable effectively utilize space to be connected with propulsion subsystem; Top board and Weighing module base plate are with bolts, and Weighing module prolongs adapter ring radial arrangement, and 4 tunnel modules are uniform by 90 degree.One of them fixed Weighing module and relative an installation of semi-floating Weighing module, another two fixed Weighing modules are installed relatively, are distributed on adapter ring.Weighing module top board and test are with bolts between adapter ring.Thermal insulation board is arranged on Weighing module medial surface, thus the impact of the radiation heat that minimizing propulsion subsystem main engine ignition produces on sensor.Different propulsion subsystem mounting bracket bases are made corresponding adapter ring, and the mounting hole on adapter ring is corresponding with base installing hole, with bolts.This barycenter is measured and weighing device is applied in satellite or rocket Upper Stage propulsion subsystem engine ignition process, can measure real-time propellant waste, can measure barycenter again.
The present invention's advantage is compared with prior art:
(1) this application of installation is in the test of satellite or rocket Upper Stage propulsion subsystem engine ignition, is to weigh and effective combination of barycenter measuring technique and space experiment.
(2) propellant waste can be measured in real time, barycenter can be measured again.
Accompanying drawing explanation
Fig. 1 is that propulsion subsystem barycenter is measured and weighing device construction profile
Fig. 2 is that propulsion subsystem barycenter is measured and weighing device plan structure figure
Fig. 3 is that adapter ring is demarcated panel plan structure figure
Fig. 4 is that adapter ring is demarcated panel construction profile
Fig. 5 is Weighing module thermal insulation board plan structure figure
Fig. 6 is Weighing module thermal insulation board construction profile
In Fig. 1:
1. adapter ring 2. thermal insulation board 3. Weighing module 4. top board 5. joist steel 6. base plates
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail.
Apparatus structure of the present invention as shown in Figure 1, comprises adapter ring (1), thermal insulation board (2), Weighing module (3), top board (4), joist steel (5), base plate (6); Structure is as shown in Fig. 3 Fig. 4: adapter ring is demarcated panel; Structure is as shown in Fig. 5 Fig. 6: Weighing module thermal insulation board.
First according to satellite or rocket Upper Stage propulsion subsystem weighing load, adapter ring (1), top board (4), joist steel (5), base plate (6) are checked to design, top board (4) is carried out to welding production by joist steel (5) with base plate (6) and become bearing bracket, after completing, bearing bracket is carried out to gravity impulse test, and load weight is 2 times of real load value.After impulse test completes, detected a flaw in top board (4), joist steel (5), each position of base plate (6), after qualified, bearing bracket is lifted on test two-layer platform, base plate annulus is welded on two layers of test cell strengthening steel slab, has the circular hole for Upper Stage propulsion subsystem main engine ignition on steel plate.Top board (4) is with bolts with Weighing module (3) base plate, and Weighing module (3) prolongs adapter ring (1) radial arrangement, and 4 tunnel modules are uniform by 90 degree.One of them fixed Weighing module and relative an installation of semi-floating Weighing module, another two fixed Weighing modules are installed relatively, are distributed on adapter ring.Weighing module (3) top board and test are with bolts between adapter ring (1).Thermal insulation board (2) is arranged on Weighing module medial surface.
Adapter ring is demarcated to panel and be placed on adapter ring (1) above, adopt national secondary scale calibrating mode, by real load weight, Weighing module is demarcated to calibration.Pass through heavy frame and each parts Joint regulation until meet test mission book weighing technology index, Zai You metrological service provides relevant certificate of measurement and weight.
Calibrate qualified after, take off adapter ring and demarcate panel.Satellite or rocket Upper Stage are installed to adapter ring (1) above, by measuring the weight of single Weighing module, calculate propulsion subsystem centroid position point and Upper Stage propulsion subsystem general assembly (TW).In repropellenting process, by the measurement to Upper Stage propulsion subsystem general assembly (TW), calculate the adding amount of propellant.After oxygenant and fuel adding complete, again calculate propulsion subsystem centroid position.In engine ignition process, according to operating condition of test, measure in real time propellant waste, and the side-play amount of the rear Upper Stage propulsion subsystem barycenter of each test.After all off-tests, by the measurement of Upper Stage propulsion subsystem general assembly (TW), calculate the total flow of propellant and the amount of squeezing back of aftertreatment.So far, the measurement of Upper Stage propulsion subsystem barycenter and weighing measurement work all finish.
The present invention not detailed description is known to the skilled person technology.
Claims (1)
- A satellite or rocket Upper Stage propulsion subsystem barycenter measure and the device of weighing by: base plate, joist steel, top board, Weighing module, thermal insulation board, adapter ring form; Wherein Weighing module consists of the stop means on top board, top board, base plate, 0745 stainless steel welded seal LOAD CELLS, sensor connecting piece;Base plate annulus is welded on two layers of test cell strengthening steel slab, has the circular hole for Upper Stage propulsion subsystem main engine ignition on steel plate; Joist steel and top board weld, and adopt joist steel can make propellant fill-drain lines road, distribution pipeline and measurement and control cable effectively utilize space to be connected with propulsion subsystem; Top board and Weighing module base plate are with bolts, and Weighing module prolongs adapter ring radial arrangement, and 4 tunnel modules are uniform by 90 degree; One of them fixed Weighing module and relative an installation of semi-floating Weighing module, another two fixed Weighing modules are installed relatively, are distributed on adapter ring; Weighing module top board and test are with bolts between adapter ring; Thermal insulation board is arranged on Weighing module medial surface, thus the impact of the radiation heat that minimizing propulsion subsystem main engine ignition produces on sensor; Different propulsion subsystem mounting bracket bases are made corresponding adapter ring, and the mounting hole on adapter ring is corresponding with base installing hole, with bolts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420028573.0U CN203949788U (en) | 2014-01-17 | 2014-01-17 | The device that a kind of satellite or rocket Upper Stage propulsion subsystem barycenter are measured and weighed |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420028573.0U CN203949788U (en) | 2014-01-17 | 2014-01-17 | The device that a kind of satellite or rocket Upper Stage propulsion subsystem barycenter are measured and weighed |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203949788U true CN203949788U (en) | 2014-11-19 |
Family
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420028573.0U Expired - Fee Related CN203949788U (en) | 2014-01-17 | 2014-01-17 | The device that a kind of satellite or rocket Upper Stage propulsion subsystem barycenter are measured and weighed |
Country Status (1)
| Country | Link |
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| CN (1) | CN203949788U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105628303A (en) * | 2015-12-25 | 2016-06-01 | 南京理工大学 | Cubesat centroid measurement method |
| CN106014691A (en) * | 2016-07-29 | 2016-10-12 | 北京航天试验技术研究所 | Vacuum-thrust-vector measurement system capable of adjusting rocket-motor swinging direction in real time |
| CN106124125A (en) * | 2015-05-04 | 2016-11-16 | 梅特勒-托利多(常州)测量技术有限公司 | Barycenter Weighing system |
| CN106516167A (en) * | 2016-11-03 | 2017-03-22 | 上海卫星工程研究所 | High precision propellant filling method for high orbit satellite with parallel-connection flat-laid storage tanks |
| CN106525438A (en) * | 2016-11-03 | 2017-03-22 | 北京航天试验技术研究所 | Planar annular heavy load force bearing device for liquid rocket power system test |
| RU2770896C1 (en) * | 2021-09-13 | 2022-04-25 | Акционерное общество "Конструкторское бюро химавтоматики" | Method for determining the coordinates of the center of mass of the product |
-
2014
- 2014-01-17 CN CN201420028573.0U patent/CN203949788U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106124125A (en) * | 2015-05-04 | 2016-11-16 | 梅特勒-托利多(常州)测量技术有限公司 | Barycenter Weighing system |
| CN105628303A (en) * | 2015-12-25 | 2016-06-01 | 南京理工大学 | Cubesat centroid measurement method |
| CN105628303B (en) * | 2015-12-25 | 2019-11-15 | 南京理工大学 | Cube centroid of satellite measurement method |
| CN106014691A (en) * | 2016-07-29 | 2016-10-12 | 北京航天试验技术研究所 | Vacuum-thrust-vector measurement system capable of adjusting rocket-motor swinging direction in real time |
| CN106014691B (en) * | 2016-07-29 | 2018-08-31 | 北京航天试验技术研究所 | A kind of vacuum thrust vector measurement system that can be adjusted rocket engine in real time and wave direction |
| CN106516167A (en) * | 2016-11-03 | 2017-03-22 | 上海卫星工程研究所 | High precision propellant filling method for high orbit satellite with parallel-connection flat-laid storage tanks |
| CN106525438A (en) * | 2016-11-03 | 2017-03-22 | 北京航天试验技术研究所 | Planar annular heavy load force bearing device for liquid rocket power system test |
| CN106516167B (en) * | 2016-11-03 | 2019-05-03 | 上海卫星工程研究所 | The high-precision repropellenting method of high rail parallel connection tiling tank satellite |
| RU2770896C1 (en) * | 2021-09-13 | 2022-04-25 | Акционерное общество "Конструкторское бюро химавтоматики" | Method for determining the coordinates of the center of mass of the product |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141119 Termination date: 20170117 |