CN101539465A - Propellant pipeline connecting device based on elastic axis - Google Patents
Propellant pipeline connecting device based on elastic axis Download PDFInfo
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- CN101539465A CN101539465A CN200910083033A CN200910083033A CN101539465A CN 101539465 A CN101539465 A CN 101539465A CN 200910083033 A CN200910083033 A CN 200910083033A CN 200910083033 A CN200910083033 A CN 200910083033A CN 101539465 A CN101539465 A CN 101539465A
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- propellant
- elastic shaft
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Abstract
The invention discloses a propellant pipeline connecting device based on an elastic axis, comprising a frame, the elastic axis, a cantilever beam, an engine, a propellant rigid pipe, a propellant hose, a displacement sensor and a bracket, wherein the frame is cubical structure, both ends of the elastic axis are installed on the frame via bolts, the elastic axis is machined with a flange and is further provided with a hole, one end of the cantilever beam is installed on the elastic axis via the flange of the elastic axis, the other end of the cantilever beam is fixed with the bracket via bolts, one end of the displacement sensor is connected with the bracket, the other end of the displacement sensor is fixed at the upper end of a support bar, the lower end of the support bar is fixed on the frame, and the engine is fixed on the bracket; one end of the propellant rigid pipe is connected with the engine, the other end of the propellant rigid pipe is connected with the propellant hose via an adaptor, and the adaptor is installed and fixed in an interference way through the hole of the elastic axis; and the invention has simple structure, easy realization and easy operation, and the measuring result of microthrust is the actual thrust of engine by assembling the elastic axis and the propellant supplying pipeline in microthrust measurement.
Description
Technical field
The present invention relates to a kind of propellant pipeline coupling arrangement, belong to space propulsion thrust measurement technical field based on elastic shaft.
Background technology
Spaces such as little, electric propulsion all are widely used in many fields such as Aero-Space with the thrust engine with tiny technology, the measuring micro-thrust technology is a gordian technique in the engines ground test, the thrust of having only the actual measurement of obtaining, just can obtain the actual performance parameter (the engine actual specific is dashed) of engine, and carry out further design and development work.
Because the thrust very little (mN level or μ N level) during thrust engine with tiny work, the connection of propellant pipeline produces very big influence to the measurement of thrust again, can produce high temperature during engine operation, and whole engine must be worked under vacuum, thereby brings very big difficulty for the direct measurement of thrust.
Summary of the invention
The object of the present invention is to provide a kind of propellant pipeline coupling arrangement based on elastic shaft, when propellant being provided for the space propulsion that carries out the thrust test, have any impact for the thrust measurement of engine, for thrust engine with tiny, any disturbance will cause very big measuring error to the thrust of engine, even can cause the thrust measurement mistake.
A kind of propellant pipeline coupling arrangement based on elastic shaft of the present invention comprises: framework, elastic shaft, semi-girder, engine, propellant rigid pipe, propellant flexible pipe, displacement transducer and support;
Described framework is a cube structure, supports upper and lower two installing plates by four bars and forms, and between the upper and lower installing plate of described framework elastic shaft is installed, and framework uses the lower margin screw retention on surface level by the foot screw hole on the lower installation board;
The upper mounted plate at elastic shaft two ends and bottom plate are installed on the upper mounting plate and lower installation board of framework by bolt, be processed with ring flange on the described elastic shaft, be used for fixing semi-girder, also have a hole on the elastic shaft, the central axis in described hole is vertical with the center line of elastic shaft, is used for fixing the adapter that connects propellant flexible pipe and propellant rigid pipe;
One end of semi-girder is installed on the elastic shaft by the ring flange on the elastic shaft, the other end has support with bolt, one end of displacement transducer is fixed on the support, the other end is fixed on post upper, the support bar lower end is by on the lower installation board that is bolted to framework, and engine also is fixed on the support;
Propellant rigid pipe one end connects engine, and the other end connects the propellant flexible pipe by adapter, and described adapter is by the hole interference mount of elastic shaft.
The invention has the advantages that:
(1) adopt comparatively simply device, elastic shaft and propellant feed pipeline assembled during microthrust was measured, and can make the microthrust measurement result is the actual thrust of engine;
(2) apparatus of the present invention are easy to realize easy operating.
Description of drawings
Fig. 1 is the structural representation of a kind of propellant pipeline coupling arrangement based on elastic shaft of the present invention;
Fig. 2 is the structural representation of elastic shaft of the present invention.
Among the figure:
1-framework 2-elastic shaft 3-semi-girder 4-engine
5-propellant rigid pipe 6-propellant flexible pipe 7-displacement transducer 8-support
9-support bar 101-upper mounting plate 102-lower installation board 103-foot screw hole
201-upper mounted plate 202-bottom plate 203-ring flange 204-hole
Embodiment
The present invention is described in further detail below in conjunction with accompanying drawing.
The present invention is a kind of propellant pipeline coupling arrangement based on elastic shaft, as shown in Figure 1, comprising: framework 1, elastic shaft 2, semi-girder 3, engine 4, propellant rigid pipe 5, propellant flexible pipe 6, displacement transducer 7 and support 8.
The upper mounted plate 201 at elastic shaft 2 two ends and bottom plate 202 are installed on the upper mounting plate 101 and lower installation board 102 of framework 1 by bolt.As shown in Figure 2, be processed with ring flange 203 on the described elastic shaft 2, be used for fixing semi-girder 3, also have a hole 204 on the elastic shaft 2, described hole 204 central axis are vertical with the center line of elastic shaft 2, are used for fixing the adapter that connects propellant flexible pipe 6 and propellant rigid pipe 5.Elastic shaft 2 can reverse along self axis, and the windup-degree scope is positive and negative 20 °, and the unrelieved stress of elastic shaft 2 was 0 when engine 4 quit work, and elastic shaft 2 does not have unrelieved stress in repeatedly using.
One end of semi-girder 3 is installed on the elastic shaft 2 by the ring flange on the elastic shaft 2 203, the other end has support 8 with bolt, one end of displacement transducer 7 is fixed on the support 8, the other end is fixed on the upper end of support bar 9, the lower end of support bar 9 is fixed on the lower installation board 102 of framework 1, and engine 4 is fixed on the support 8;
Propellant rigid pipe 5 one ends connect engine 4, and the other end connects propellant flexible pipe 6 by adapter, and described adapter is by the hole 204 interference mounts of elastic shaft 2.The other end of described propellant flexible pipe 6 connects the required propellant of engine 4, required propellant when being used for providing work to engine 4.
Among the present invention propellant rigid pipe 5 is matched the thrust when being used to measure thrust engine with tiny 4 work with elastic shaft 2.The propellant rigid pipe 5 that connects engine 4 is an elastic tube, the fulcrum of propellant rigid pipe 5 is positioned on the axis of elastic shaft 2, propellant rigid pipe 5 is equivalent to fulcrum and is positioned at new semi-girder on elastic shaft 2 axis, under the situation of engine 4 thrusts very little (little ox level is in milli ox level scope), the anglec of rotation and the thrust of propellant rigid pipe 5 elastic shaft 2 under the effect of engine 4 thrusts are directly proportional, and promptly satisfy Hooke's law.Owing to all satisfy Hooke's law, a new elastic system is formed in new semi-girder that propellant rigid pipe 5 forms and semi-girder 3 and elastic shaft 2 stacks.
Semi-girder 3 of the present invention and propellant rigid pipe 5 are horizontal, the central axis of the central axis of described propellant rigid pipe 5 and semi-girder 3 is in same perpendicular and parallel, before engine 4 work, at first, adjust framework 1 and make semi-girder 3 and propellant rigid pipe 5 be in level, the central axis that makes propellant rigid pipe 5 and the central axis of semi-girder 3 are in same perpendicular and parallel.Then, elastic system to semi-girder 3 and propellant rigid pipe 5 and elastic shaft 2 compositions is demarcated, promptly given a different set of power from the central axis of engine 4 records corresponding displacement with displacement transducer 7, obtains the elasticity coefficient of system by the size of displacement and power.This elasticity coefficient is the combined elastic coefficient of elastic system.
When the work of engine 4, when elastic deformations took place propellant rigid pipe 5,6 pairs of elastic shafts 2 of propellant flexible pipe did not produce torsional moment, guaranteed that promptly propellant flexible pipe 6 does not produce any influence to reversing of elastic shaft 2 in engine 4 work.Elastic shaft 2 is the fulcrum of semi-girder 3, the thrust of engine 4 is in semi-girder 3, direction is perpendicular to the central axis of semi-girder 3, the distance that the thrust of engine 4 multiply by engine 4 thrust lines and elastic shaft 2 central axis is the moment of torsion that engine 4 work produce elastic shaft 2, under the effect of this moment of torsion, semi-girder 3 is with rotating certain angle, and correspondingly, elastic shaft 2 also will produce identical windup-degree.At this moment, 3 pairs of displacement transducers of semi-girder 7 produce acting force, displacement transducer 7 is measured the displacement of semi-girders 3, and the combined elastic coefficient of the elastic system that is obtained by the demarcation before engine 4 work can be according to the power that produces when displacement transducer 7 reading obtains engine 4 work this moment.
Claims (2)
1, a kind of propellant pipeline coupling arrangement based on elastic shaft is characterized in that this coupling arrangement comprises: framework, elastic shaft, semi-girder, engine, propellant rigid pipe, propellant flexible pipe, displacement transducer and support;
Described framework is a cube structure, supports upper and lower two installing plates by four bars and forms, and between the upper and lower installing plate of described framework elastic shaft is installed, and framework uses the lower margin screw retention on surface level by the foot screw hole on the lower installation board;
The upper mounted plate at elastic shaft two ends and bottom plate are installed on the upper mounting plate and lower installation board of framework by bolt, be processed with ring flange on the described elastic shaft, be used for fixing semi-girder, also have a hole on the elastic shaft, the central axis in described hole is vertical with the center line of elastic shaft, is used for fixing the adapter that connects propellant flexible pipe and propellant rigid pipe;
One end of semi-girder is installed on the elastic shaft by the ring flange on the elastic shaft, the other end has support with bolt, one end of displacement transducer is fixed on the support, the other end is fixed on post upper, the support bar lower end is by on the lower installation board that is bolted to framework, and engine is fixed on the support;
Propellant rigid pipe one end connects engine, and the other end connects the propellant flexible pipe by adapter, and described adapter is fixed by the hole interference of elastic shaft.
2, a kind of propellant pipeline coupling arrangement based on elastic shaft according to claim 1 is characterized in that: the central axis of described propellant rigid pipe and the central axis of semi-girder are in same perpendicular and parallel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009100830336A CN101539465B (en) | 2009-04-24 | 2009-04-24 | Propellant pipeline connecting device based on elastic axis |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009100830336A CN101539465B (en) | 2009-04-24 | 2009-04-24 | Propellant pipeline connecting device based on elastic axis |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101539465A true CN101539465A (en) | 2009-09-23 |
| CN101539465B CN101539465B (en) | 2010-09-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009100830336A Expired - Fee Related CN101539465B (en) | 2009-04-24 | 2009-04-24 | Propellant pipeline connecting device based on elastic axis |
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| Country | Link |
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| CN (1) | CN101539465B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102012292A (en) * | 2010-09-30 | 2011-04-13 | 清华大学 | Device for measuring micro thrust of engine |
| CN104655343A (en) * | 2015-02-09 | 2015-05-27 | 北京理工大学 | High-precision measuring method for dynamic pushing force of micro initiating explosive actuated device |
-
2009
- 2009-04-24 CN CN2009100830336A patent/CN101539465B/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102012292A (en) * | 2010-09-30 | 2011-04-13 | 清华大学 | Device for measuring micro thrust of engine |
| CN102012292B (en) * | 2010-09-30 | 2012-07-25 | 清华大学 | Device for measuring micro thrust of engine |
| CN104655343A (en) * | 2015-02-09 | 2015-05-27 | 北京理工大学 | High-precision measuring method for dynamic pushing force of micro initiating explosive actuated device |
| CN104655343B (en) * | 2015-02-09 | 2017-04-26 | 北京理工大学 | High-precision measuring method for dynamic pushing force of micro initiating explosive actuated device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101539465B (en) | 2010-09-08 |
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Granted publication date: 20100908 Termination date: 20110424 |