CN205971888U - Aircraft driving system testing arrangement - Google Patents
Aircraft driving system testing arrangement Download PDFInfo
- Publication number
- CN205971888U CN205971888U CN201620713057.0U CN201620713057U CN205971888U CN 205971888 U CN205971888 U CN 205971888U CN 201620713057 U CN201620713057 U CN 201620713057U CN 205971888 U CN205971888 U CN 205971888U
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- riser
- transverse slat
- pulling force
- flight vehicle
- power system
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Abstract
The utility model provides an aircraft driving system testing arrangement, it is including " L " shape scute, bottom sprag frame and force sensor, " L " the shape scute include the diaphragm with set up in diaphragm one end is and the perpendicular to the riser of diaphragm, " L " shape scute through the pivot rotate connect in on the bottom sprag frame, so that " L " shape scute can rotate, force sensor set up in on the diaphragm upper surface to draw surface contact on force sensor end and the diaphragm, it constructs to be provided with the driving system fixed knot that awaits measuring on the riser lateral surface of " L " shape scute. The utility model discloses an aircraft driving system testing arrangement has been owing to used " L " shape scute, and the transmission of doing all can is carried out to the principle of utilizing moment balance, can for reserving sufficient space around the screw, avoid the peripheral air current of testboard to be disturbed on the rotation plane perpendicular to diaphragm or the ground of screw to it is more accurate to make the test result.
Description
Technical field
This utility model is related to aircraft, the dynamical system unified test in more particularly, to a kind of Power System of Flight Vehicle R＆D process
Trial assembly is put.
Background technology
The dynamical system of airborne vehicle plays action of the heart in the operation of whole system, in civilian man-carrying aircraft neck
Domain, as the major part of dynamical system, shared R＆D fund and development costs are often all systems to aero-engine
Middle highest.And the performance test of dynamical system is a most important and indispensable part in R＆D process.Cause
This design a set of safety, dependable performance, cost suitable dynamical system testbed it is critical that.
However, existing propeller class dynamical system testboard peripheral gas flow is easily disturbed it is impossible to aircraft power
The performance of system is accurately tested.
Utility model content
In view of drawbacks described above of the prior art or deficiency, this utility model aims to provide a kind of testboard peripheral gas flow not
Easily it is disturbed, accurate testing flying vehicle dynamical system test device can be carried out.
Power System of Flight Vehicle test device of the present utility model, including " L " shape gusset, bottom bracing frame and pull sensing
Device；
Described " L " shape gusset includes transverse slat and is arranged at described transverse slat one end and the riser perpendicular to described transverse slat；
Described " L " shape gusset is connected in described bottom support plate by axis of rotation；
Described pulling force sensor is arranged on described transverse slat upper surface, and the pulling force induction end of pulling force sensor and transverse slat
Upper surface；
Dynamical system fixed structure to be measured is provided with the riser lateral surface of described " L " shape gusset.
Power System of Flight Vehicle test device of the present utility model, to aircraft dynamical system (include propeller and
Motor) when carrying out performance test, motor external power supply motor and propeller rotational, dynamical system to be measured can produce one and hang down
The directly pulling force to riser in riser, is connected because " L " shape gusset is rotated with bottom bracing frame, therefore rotating shaft not transmitting torque,
In order to balance the moment of torsion producing due to this pulling force, " the pulling force sensor installation end of transverse slat, pulling force sensor can be subject to by one
Urgent pressure.The reading F of therefore pulling force sensor2(it should be noted that pulling force sensor is in the not actuated poised state of dynamical system to be measured
When, reading is modified to 0) it is multiplied by corresponding coefficient C, pulling force F, i.e. F=F that dynamical system as to be measured produces2C, C=X2/X1,
X2For the vertical dimension of axial line position of the power to transverse slat apart from pulling force sensor of rotating shaft, X1For rotating shaft axial line away from
Vertical dimension from the position of the power to riser for the dynamical system to be measured.Power System of Flight Vehicle test device of the present utility model
Due to employing " L " shape gusset, carry out the transmission of power using the principle of equalising torque, can will be vertical for the Plane of rotation of propeller
In transverse slat or ground, be propeller before and after reserve enough spaces, it is to avoid because propeller Plane of rotation is put down in prior art
Ground effect caused by ground or transverse slat for the row, testboard peripheral gas flow will not be disturbed, so that test result is more accurate.
Brief description
In order to be illustrated more clearly that this utility model embodiment or technical scheme of the prior art, below will be to embodiment
Or in description of the prior art the accompanying drawing of required use be briefly described it should be apparent that, drawings in the following description are only
It is some embodiments of the present utility model, for those of ordinary skill in the art, in the premise not paying creative work
Under, other accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 is the structural representation of Power System of Flight Vehicle test device exploded state in this utility model embodiment
Figure；
Fig. 2 is the structural representation of Power System of Flight Vehicle test device in this utility model embodiment.
In figure labelling is illustrated as：
1- pulling force sensor；
21- transverse slat；
22- riser；
3- propeller；
4- motor；
5- torsion torque sensor；
6- rotating shaft；
71- bottom support plate；
72nd, 73- bearing assembly；
721- bearing block；
722- bearing；
723- bearing (ball) cover；
81- horizontal block；
82- vertical block；
9- horizontal reference block；
10- pulling force sensor fixed plate；
11-A/D modular converter；
12- ring flange.
Specific embodiment
With reference to the accompanying drawings and examples the application is described in further detail.It is understood that this place is retouched
The specific embodiment stated is used only for explaining relevant utility model, rather than the restriction to this utility model.Further need exist for explanation
, for the ease of description, in accompanying drawing, illustrate only the part related to utility model.
It should be noted that in the case of not conflicting, the embodiment in the application and the feature in embodiment can phases
Mutually combine.To describe the application below with reference to the accompanying drawings and in conjunction with the embodiments in detail.
Embodiment 1
With reference to Fig. 1 and Fig. 2, present embodiments provide a kind of Power System of Flight Vehicle test device, this aircraft power system
Guided Missiles Service Test Set includes " L " shape gusset, bottom bracing frame and pulling force sensor 1；
Described " L " shape gusset includes transverse slat 21 and is arranged at described transverse slat 21 one end and erecting perpendicular to described transverse slat 21
Plate 22；
Described " L " shape gusset is rotationally connected with the bracing frame of described bottom by rotating shaft 6, so that described " L " shape gusset energy
Enough rotations；It will be understood by those skilled in the art that described rotation refers to rotate with rotating shaft 6 for axle, and refer to " L " shape angle
The overall rotation of plate.
Described pulling force sensor 1 is arranged on described transverse slat 21 upper surface, and the pulling force induction end of pulling force sensor 1 with
Transverse slat 21 upper surface；
Described riser 22 lateral surface is provided with dynamical system fixed structure to be measured.
Power System of Flight Vehicle test device of the present utility model, to aircraft dynamical system (include propeller 3 and
Motor 4) when carrying out performance test, motor 4 external power supply motor 4 and propeller 3 rotate, and dynamical system to be measured can produce one
The individual pulling force perpendicular to riser 22 to riser 22, is rotated with bottom bracing frame by " L " shape gusset and is connected, therefore rotating shaft 6 does not pass
Torque delivery, in order to balance the moment of torsion producing due to this pulling force, in the pulling force sensor installation end of " L " shape gusset, pulling force sensor 1
Pressure can be forced to by one.The reading F of reason pulling force sensor 12(it should be noted that pulling force sensor does not open in dynamical system to be measured
During dynamic poised state, reading is modified to 0) it is multiplied by corresponding coefficient C, pulling force F, i.e. F=that dynamical system as to be measured produces
F2C, C=X2/X1, X2For the vertical dimension of axial line position of the power to transverse slat 21 apart from pulling force sensor 1 of rotating shaft 6, X1
Vertical dimension for axial line position of the power to riser 22 apart from dynamical system to be measured of rotating shaft 6.Above-mentioned aircraft moves
Force system test device, due to employing " L " shape gusset, carries out the transmission of power using the principle of equalising torque, can be by propeller
3 Plane of rotation perpendicular to transverse slat 21 or ground, be propeller 3 before and after reserve enough spaces, it is to avoid in prior art
Because propeller 3 Plane of rotation is parallel to the ground effect caused by ground or transverse slat 21, it is to avoid testboard peripheral gas flow is disturbed,
So that test result is more accurate.
In the present embodiment, further, optionally, described rotating shaft 6 is arranged at transverse slat 21 and the riser of described " L " shape gusset
At 22 joint angle.It is arranged such, described dynamical system test device structure can be made more stable, design is also more reasonable.
In another optional embodiment of the present embodiment, described Power System of Flight Vehicle test device also includes torsion and passes
Sensor 5；
Described torsion torque sensor 5 one end is fixed on described dynamical system fixed structure to be measured, and the other end is treated for connection
Survey dynamical system, be arranged such, the torsion that dynamical system to be measured produces can directly be measured by torsion torque sensor 5 so that this reality
Apply the Power System of Flight Vehicle test device in example and have and can the pulling force and torsion of dynamical system to be measured be tested simultaneously
Advantage.
In the present embodiment, optionally, it is provided with contiguous block at the joint angle of described transverse slat 21 and riser 22；
Described rotating shaft 6 is arranged in described contiguous block and extends to from the joint angle side of transverse slat 21 and riser 22 another
Side；
Described bottom bracing frame includes bottom support plate 71 and bearing assembly 72,73；
Described rotating shaft 6 one end is installed on described bottom support plate 71 upper surface by bearing assembly 72, and the other end passes through
Bearing assembly 73 is installed on described bottom support plate 71 upper surface, is arranged such, can be by rotating shaft 6 two ends and bottom support plate
71 is fixing, so that " L " shape gusset can rotate.
More specifically, the bearing assembly 72,73 in the present embodiment all includes bearing block 721, bearing 722 and bearing (ball) cover
723, when specifically installing, bearing block 721 bottom is fixed in bottom support plate 71 by threaded fastener, bearing 722 loads
In bearing block 721, and rotating shaft 6 end is fixed in bearing 722, then covers bearing (ball) cover 723.
In the present embodiment, further, described contiguous block is arranged at the interior joint angle that transverse slat 21 and riser 22 are formed,
So that whole Power System of Flight Vehicle test device structure is more firm.Described " interior joint angle " refers to the transverse slat 21 of " L " shape gusset
The angle being formed with riser 22.
In the present embodiment, further, described contiguous block is " L " shape contiguous block, and it is identical that " L " shape contiguous block includes shape
Horizontal block 81 and vertical block 82；
Described horizontal block 81 is fixed together with described transverse slat 21, and described vertical block 82 is fixed together with described riser 22, institute
State rotating shaft 6 to be arranged at the junction of horizontal block 81 and vertical block 82 and be through to opposite side from the side of contiguous block, to make described
Rotating shaft 6 is placed exactly at the interior joint angle that transverse slat 21 and riser 22 are formed.
Above-mentioned vertical block 82 can be fixed together with described riser 22 by threaded fastener, and described horizontal block 81 can also
It is fixed together with transverse slat 21 by threaded fastener, is arranged such, there is structure simply, the advantage being fixed conveniently.
In addition, in the present embodiment, optionally, below the transverse slat 21 of described " L " shape gusset one end away from described joint angle
It is arranged at and is provided with horizontal reference block 9 and described bottom support plate 71 between, so that transverse slat 21 keeps level, due to described transverse slat
21 one end being provided with riser 22 are passed through bearing block 721 and are fixed, and this end lower surface described has a spacing with bottom support plate 71
From, and described transverse slat 21 holding level will be made, can be adjusted by way of horizontal reference block 9 is set.
Described horizontal reference block 9 can reinforce the upper surface due to described bottom support plate 71 by threaded fastener.
In the present embodiment, optionally, described pulling force sensor 1 is arranged on described transverse slat 21 upper surface and is located at transverse slat
21 away from described joint angle one end so that described pulling force sensor 1 has larger distance apart from rotating shaft 6, with improve test essence
Degree.
In addition, in the present embodiment, optionally, described bottom support plate 71 upper surface is fixed with pulling force sensor fixed plate
10, the side of described pulling force sensor 1 is fixed in described pulling force sensor fixed plate 10, and described pulling force sensor 1 can lead to
Cross threaded fastener to be fixed in described pulling force sensor fixed plate 10.
In the present embodiment, more specifically, described dynamical system fixed structure to be measured can be vertically solid by dynamical system to be measured
On the lateral surface of described " L " shape gusset, and the axial line of rotating shaft 6 can be made to riser 22 apart from dynamical system to be measured
The vertical dimension of the position of power is vertical with axial line position of the power to transverse slat 21 apart from pulling force sensor 1 of rotating shaft 6
Apart from equal, i.e. C=X2/X1=1, it is arranged such, the reading F of pulling force sensor 12It is the pulling force that dynamical system to be measured produces,
Need not be calculated by formula, have the advantages that directly perceived and convenient.During concrete setting, can be by the motor of dynamical system to be measured
4 are directly perpendicularly fixed at by dynamical system fixed structure to be measured on the lateral surface of riser 22 of described " L " shape gusset, and make
Motor 4 is contacted with riser 22 away from one end of propeller, and in propeller 3 rotation process, dynamical system to be measured is directly to riser 22
Produce pulling force, be arranged such, the position of the axial line of motor 4 and the power to riser 22 for the dynamical system to be measured is in straight line
On, the axial line of rotating shaft 6 apart from motor 4 axial line vertical dimension and rotating shaft 6 apart from pulling force sensor 1 to the power of transverse slat 21
The vertical dimension of position is equal.
In addition, optional, the torque sensing end of described torsion torque sensor 5 is arranged towards the direction away from riser 22, so that more
Accurately measure the torsion that dynamical system to be measured produces；
Described electric machine fixation structure is ring flange 12；
The other end of described torsion torque sensor 5 is fixed on the outside of described riser 22 by described ring flange, is arranged such,
There is structure simple, the advantage being fixed conveniently.
In the present embodiment, optionally, described transverse slat 21 and riser 22 shape and equivalently-sized, so that flying in the present embodiment
Row device dynamical system test device structure is compacter and firm.
In addition, described Power System of Flight Vehicle test device, can also include being connected A/D with described torsion torque sensor 5
Modular converter 11, by described A/D modular converter 11 can by the signal of telecommunication of torsion torque sensor 5 be converted into digital signal carry out defeated
Go out.
Described A/D modular converter 11 can be fixed on the medial surface of described riser 22.
Described " medial surface of riser 22 " refers to riser 22 face adjacent with transverse slat 21 upper surface, in the present embodiment, described " perpendicular
The lateral surface of plate 22 " refers to the face paralleled with the medial surface of riser.
Above description is only the preferred embodiment of the application and the explanation to institute's application technology principle.People in the art
Member is it should be appreciated that involved utility model scope is however it is not limited to the particular combination of above-mentioned technical characteristic in the application
Technical scheme, also should cover simultaneously without departing from described utility model design in the case of, by above-mentioned technical characteristic or its be equal to
Other technical schemes that feature carries out combination in any and formed.Such as features described above is had with (but not limited to) disclosed herein
The technical scheme that the technical characteristic having similar functions is replaced mutually and formed.
Claims (13)
1. a kind of Power System of Flight Vehicle test device passes it is characterised in that including " L " shape gusset, bottom bracing frame and pulling force
Sensor；
Described " L " shape gusset includes transverse slat and is arranged at described transverse slat one end and the riser perpendicular to described transverse slat；
Described " L " shape gusset is connected on the bracing frame of described bottom by axis of rotation；
Described pulling force sensor is arranged on described transverse slat upper surface, and the pulling force induction end of pulling force sensor and transverse slat upper table
Face contacts；
Dynamical system fixed structure to be measured is provided with the riser lateral surface of described " L " shape gusset.
2. Power System of Flight Vehicle test device according to claim 1 it is characterised in that described rotating shaft be arranged at described
At the transverse slat of " L " shape gusset and the joint angle of riser.
3. Power System of Flight Vehicle test device according to claim 2 is it is characterised in that also include torsion torque sensor；
Described torsion torque sensor one end is fixed on described dynamical system fixed structure to be measured, and the other end is used for connecting power to be measured
System.
4. Power System of Flight Vehicle test device according to claim 3 is it is characterised in that the company of described transverse slat and riser
Connect and at angle, be provided with contiguous block；
Described rotating shaft is arranged in described contiguous block and extends to opposite side from the joint angle side of transverse slat and riser；
Described bottom bracing frame includes bottom support plate and bearing assembly；
Described rotating shaft two ends are installed on described bottom support plate upper surface by described bearing assembly respectively.
5. Power System of Flight Vehicle test device according to claim 4 is it is characterised in that described contiguous block is arranged at horizontal stroke
At the interior joint angle of plate and riser formation.
6. Power System of Flight Vehicle test device according to claim 5 is it is characterised in that described contiguous block is " L " shape
Contiguous block, " L " shape contiguous block includes shape identical horizontal block and vertical block；
Described horizontal block is fixed together with described transverse slat, and described vertical block is fixed together with described riser；
Described rotating shaft is arranged at the junction of horizontal block and vertical block and is through to opposite side from the side of contiguous block.
7. Power System of Flight Vehicle test device according to claim 4 is it is characterised in that the horizontal stroke of described " L " shape gusset
Plate is provided with horizontal reference block away from below one end of described joint angle and bottom support plate between.
8. the Power System of Flight Vehicle test device according to any one of claim 2-7 is it is characterised in that described pulling force passes
Sensor is arranged on described transverse slat upper surface and is located at transverse slat one end away from described joint angle.
9. Power System of Flight Vehicle test device according to claim 8 is it is characterised in that described bottom support plate upper table
Pulling force sensor fixed plate is fixed with face, the side of described pulling force sensor is fixed in described pulling force sensor fixed plate.
10. the Power System of Flight Vehicle test device according to any one of claim 3-7 is it is characterised in that described to be measured
Dynamical system to be measured can be perpendicularly fixed on the lateral surface of described riser for dynamical system fixed structure, and can make rotating shaft
Axial line apart from dynamical system to be measured, the vertical dimension of the position of the power to riser and the axial line of rotating shaft pass apart from pulling force
The vertical dimension of the position of the power to transverse slat for the sensor is equal.
11. Power System of Flight Vehicle test devices according to claim 10 are it is characterised in that described torsion torque sensor
Torque sensing end is towards the direction setting away from riser；
Described dynamical system electric machine fixation structure to be measured is ring flange；
The other end of described torsion torque sensor is fixed on the outside of described riser by described ring flange.
12. Power System of Flight Vehicle test devices according to any one of claim 1-7 are it is characterised in that described transverse slat
With riser shape and equivalently-sized.
13. Power System of Flight Vehicle test devices according to any one of claim 3-7 it is characterised in that also include with
The A/D modular converter that described torsion torque sensor connects.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620713057.0U CN205971888U (en) | 2016-07-07 | 2016-07-07 | Aircraft driving system testing arrangement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620713057.0U CN205971888U (en) | 2016-07-07 | 2016-07-07 | Aircraft driving system testing arrangement |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205971888U true CN205971888U (en) | 2017-02-22 |
Family
ID=58023578
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620713057.0U Active CN205971888U (en) | 2016-07-07 | 2016-07-07 | Aircraft driving system testing arrangement |
Country Status (1)
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|---|---|
| CN (1) | CN205971888U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106768565A (en) * | 2017-03-09 | 2017-05-31 | 北京尖翼科技有限公司 | A kind of test device of small-sized unmanned aircraft motor |
| CN107024310A (en) * | 2017-06-01 | 2017-08-08 | 上海未来伙伴机器人有限公司 | A kind of Power System of Flight Vehicle test device |
| CN107585326A (en) * | 2016-07-07 | 2018-01-16 | 顺丰科技有限公司 | Power System of Flight Vehicle test device |
| CN107719696A (en) * | 2017-09-12 | 2018-02-23 | 北京航空航天大学 | A kind of dynamic characteristics synchronous testing device of axially compact type aircraft propeller |
| CN108216695A (en) * | 2018-01-08 | 2018-06-29 | 哈尔滨工业大学 | A kind of pendulum model Mars unmanned plane rotor system hovering characteristic test device |
| CN110823506A (en) * | 2019-10-30 | 2020-02-21 | 上海理工大学 | Wing simulation test bed driven by linear motor |
-
2016
- 2016-07-07 CN CN201620713057.0U patent/CN205971888U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107585326A (en) * | 2016-07-07 | 2018-01-16 | 顺丰科技有限公司 | Power System of Flight Vehicle test device |
| CN106768565A (en) * | 2017-03-09 | 2017-05-31 | 北京尖翼科技有限公司 | A kind of test device of small-sized unmanned aircraft motor |
| CN106768565B (en) * | 2017-03-09 | 2022-08-23 | 北京尖翼科技有限公司 | Testing arrangement of small-size unmanned vehicles motor |
| CN107024310A (en) * | 2017-06-01 | 2017-08-08 | 上海未来伙伴机器人有限公司 | A kind of Power System of Flight Vehicle test device |
| CN107719696A (en) * | 2017-09-12 | 2018-02-23 | 北京航空航天大学 | A kind of dynamic characteristics synchronous testing device of axially compact type aircraft propeller |
| CN108216695A (en) * | 2018-01-08 | 2018-06-29 | 哈尔滨工业大学 | A kind of pendulum model Mars unmanned plane rotor system hovering characteristic test device |
| CN110823506A (en) * | 2019-10-30 | 2020-02-21 | 上海理工大学 | Wing simulation test bed driven by linear motor |
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Effective date of registration: 20210722 Address after: 518063 5th floor, block B, building 1, software industry base, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province Patentee after: Fengyi Technology (Shenzhen) Co.,Ltd. Address before: 518061 Intersection of Xuefu Road (south) and Baishi Road (east) in Nanshan District, Shenzhen City, Guangdong Province, 6-13 floors, Block B, Shenzhen Software Industry Base Patentee before: SF TECHNOLOGY Co.,Ltd. |
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| TR01 | Transfer of patent right |