CN206466191U - Duct Aerospace vehicle test device - Google Patents
Duct Aerospace vehicle test device Download PDFInfo
- Publication number
- CN206466191U CN206466191U CN201720054160.3U CN201720054160U CN206466191U CN 206466191 U CN206466191 U CN 206466191U CN 201720054160 U CN201720054160 U CN 201720054160U CN 206466191 U CN206466191 U CN 206466191U
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- CN
- China
- Prior art keywords
- duct
- cross bar
- force cell
- lifting platform
- test device
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Abstract
The utility model discloses a kind of duct Aerospace vehicle test device, be applicable to the thrust of duct aircraft and it is pneumatic test, including external stability frame, slide rail, lifting platform, force cell and computer.The above-below direction of slide rail externally fixed mount is arranged at external stability frame opposite sides；Be provided with lifting platform with slide rail coordinate sliding block, lifting platform under the cooperation of sliding block and slide rail can opposite outer fixed part move up and down；One end of force cell is fixed on external stability frame, and the other end of force cell is connected with lifting platform；Computer is electrically connected with force cell, pressure or pulling force that computer is surveyed according to force cell and the thrust and pneumatic state that simulate duct aircraft, to realize the thrust to duct aircraft and the purpose of pneumatic carry out real-time testing, so as to improve test accuracy.
Description
Technical field
The utility model relates to duct vehicle technology field, relates more specifically to a kind of duct Aerospace vehicle test device.
Background technology
At present, duct aircraft is just turning into both at home and abroad to one of small-sized manned vehicle or the focus of unmanned plane research, contains
The design of the structure and control system of road aircraft all relies on its thrust and aerodynamic parameter, and duct can discharge high speed gas when working
Stream, air-flow, which is directly blowed to, to be squeezed behind ground and is spread along ground toward surrounding, and influence of this pneumatic phenomenon to duct thrust is very
Greatly, the pneumatic test of duct refers to change of the vertical duct thrust with height, by measuring the vertical duct thrust under different height
Value, influence of the research ground level to duct thrust, when needing to test the aerodynamic parameter of duct aircraft, study its thrust and
Design of the pneumatic situation to duct aircraft provides necessary guidance, and traditional method is to be utilized respectively sensor to fly duct
Each part of row device measures and obtains measurement data, due to duct aircraft and non-ideal model, each power part it
Between between supporting construction all exist influence each other, therefore, by the data individually tested carry out integrated calculating when can exist it is very big
Error, aerodynamic parameter is inaccurate, and the design of integrated model can be caused unreasonable.
Therefore, it is badly in need of a kind of duct Aerospace vehicle test that real-time thrust and pneumatic parameter testing are carried out to duct aircraft
Device overcomes above-mentioned defect.
Utility model content
The purpose of this utility model be to provide it is a kind of duct aircraft is carried out real-time thrust and pneumatic parameter testing with
Improve the duct Aerospace vehicle test device of test result accuracy.
To achieve the above object, the utility model provides a kind of duct Aerospace vehicle test device, is applicable and duct is flown
The thrust of device and it is pneumatic tested, including external stability frame, slide rail, lifting platform, force cell and computer.The slide rail
It is arranged in along the above-below direction of the external stability frame at the external stability frame opposite sides；The lifting platform is used to fix institute
State duct aircraft and in the external stability frame, the sliding block coordinated with the slide rail, institute are installed on the lifting platform
Lifting platform relatively described external stability frame under being slidably matched of the sliding block and slide rail is stated to move up and down；The force cell
One end be fixed on the external stability frame, the other end of the force cell is connected with the lifting platform；It is described to calculate
Machine is electrically connected with the force cell, computer mould according to the pressure surveyed or pulling force of the force cell
Draw up the thrust and pneumatic state of the duct aircraft.
Compared with prior art, by the cooperation of computer of the present utility model, lifting platform and force cell, therefore
When carrying out thrust and pneumatic test to duct aircraft, duct aircraft is first fixed on the liter under the first height by testing crew
Drop platform simultaneously opens duct aircraft, and the pressure or pulling force of the duct aircraft under the first height are measured by force cell, so that
Duct aircraft is obtained in the thrust under the first height by computer；Then, close duct aircraft and adjust lifting platform to the
Two height, are then turned on duct aircraft, the pressure or pulling force of the duct aircraft under the second height are measured by force cell, from
And duct aircraft is obtained in the thrust under the second height by computer；Constantly tested by adjusting the height of lifting platform,
The real-time aerodynamic condition of duct aircraft is finally simulated according to obtained experimental data by computer, is flown so as to improve duct
The thrust of row device and pneumatic accuracy.Again due to duct Aerospace vehicle test device of the present utility model include external stability frame,
Slide rail, lifting platform, force cell and computer duct Aerospace vehicle test device just can in real time to duct aircraft thrust
And it is pneumatic tested so that the simple in construction of duct Aerospace vehicle test device of the present utility model, cost it is low and test letter
Just.
It is preferred that the external stability frame includes space framework, the bottom plate being placed at the bottom of the space framework and use
In the support rail installed for the force cell, the bottom plate covers the opening of the bottom of the space framework, the cunning
Rail is located at the left and right sides of the space framework respectively, and the lifting platform is located in the space framework, and the support rail is in
Height adjustable, which saves land, to be assembled at the front and rear sides of the space framework.
It is preferred that the space framework includes 12 head and the tail in 14 aluminium alloy extrusions, 14 aluminium alloy extrusions
Docking and left and right that remainder 2 that structure goes out in rectangular box, 14 aluminium alloy extrusions is respectively supported at the rectangular box
At both sides, the slide rail is located at the left and right sides of the rectangular box respectively, and the support rail saves land assembling in height adjustable
At the front and rear sides of the rectangular box.
It is preferred that the surrounding of the aluminium alloy extrusions has the guide groove of indent.
It is preferred that the lifting platform includes left cross bar, right cross bar, front rail and rear transverse rod, the sliding block is respectively arranged in
On the left cross bar and right cross bar, the left cross bar and right cross bar are slidedly arranged on the slide rail by the sliding block, described preceding horizontal
Bar and rear transverse rod are across the left cross bar and right cross bar, and the force cell is connected to the support rail and the left side
Between cross bar and between the support rail and the right cross bar.
It is preferred that the front rail and rear transverse rod are adjustably placed on the left cross bar and right cross bar in front and back position.
It is preferred that the force cell be four and be respectively arranged in the junction of the left cross bar and support rail and
The junction of the right cross bar and support rail.
By following description and with reference to accompanying drawing, the utility model will become more fully apparent, and these accompanying drawings are used to explain this
The embodiment of utility model.
Brief description of the drawings
Fig. 1 is the dimensional structure diagram of duct Aerospace vehicle test device of the present utility model.
Fig. 2 is dimensional structure diagram of the duct Aerospace vehicle test device after lifting platform is hidden shown in Fig. 1.
Three-dimensional knot when Fig. 3 fits together for the lifting platform and sliding block in the duct Aerospace vehicle test device shown in Fig. 1
Structure schematic diagram.
Fig. 4 is the partial enlarged drawing of part A in Fig. 1.
Fig. 5 is the partial enlarged drawing of part B in Fig. 1.
Embodiment
Element numbers similar in embodiment of the present utility model, accompanying drawing, which are described, with reference now to accompanying drawing represents similar member
Part.
Fig. 1 is refer to, duct Aerospace vehicle test device 100 of the present utility model can in real time be pushed away to duct aircraft
Power and pneumatic parameter testing, with simple in construction, test simplicity and the accurate advantage of test result.
As shown in Figure 1 to Figure 3, duct Aerospace vehicle test device 100 of the present utility model includes external stability frame 10, slide rail
20th, lifting platform 30, force cell 50 and computer (not shown).Specifically, in the present embodiment, external stability frame 10 is included
Space framework 11, the bottom plate 13 being placed at the bottom of space framework 11 and the support rail for being installed for force cell 50
15, bottom plate 13 covers the opening of the bottom of space framework 11, and the high velocity air of duct aircraft discharge can be caused uniformly to spread, subtracted
The interference of few ground and the bottom of space framework 11 to air-flow, improves experimental precision；Support rail 15 saves land in height adjustable
(i.e. in figure shown in K) is assembled at the front and rear sides of space framework 11, support rail 15 is easily and flexibly adjusted relative to solid
The height of framework 11, the need for meeting experiment；Certainly, in other embodiments, external stability frame 10 can be structure as a whole, therefore not
It is limited with above-mentioned citing.Specifically, as shown in Fig. 2 in the present embodiment, space framework 11 includes 14 aluminium alloy extrusions
12 head and the tail in 111,14 aluminium alloy extrusions 111 are docked and structure goes out rectangular box, using rectangular box so that simple in construction
It is because its is easy to process and density is small, so that space framework 11 is easy to group using aluminium alloy extrusions 111 and cost is low
Dress, light weight and convenient transport；It is remaining 2 pieces points in 14 aluminium alloy extrusions 111 to cause the stress of space framework 11 more stable
It is not supported at the left and right sides of rectangular box (i.e. in figure shown in H).Bottom plate 13 covers the opening of the bottom of rectangular box, support
Cross bar 15 saves land in height adjustable to be assembled at the front and rear sides of rectangular box (i.e. in figure shown in K)；For example, such as Fig. 4 institutes
Show, in the present embodiment, the surrounding of aluminium alloy extrusions 111 has the guide groove 113 of indent, is easy to fix using bolt, but not with
This is limited.
As shown in Figure 1 to Figure 2, the above-below direction of the externally fixed mount 10 of slide rail 20 is arranged in external stability frame 10 relative two
At side；Specifically, in the present embodiment, because external stability frame 10 includes space framework 11, bottom plate 13 and support rail 15,
Therefore slide rail 20 is located at the left and right sides (i.e. in figure shown in H) of space framework 11 respectively, is preferably, slide rail 20 is located at rectangle respectively
The left and right sides of framework.
As shown in Figures 1 and 3, in the externally-located fixed mount 10 of lifting platform 30, it is provided with and matches somebody with somebody with slide rail 20 on lifting platform 30
The sliding block 40 of conjunction, the opposite outer fixed mount 10 under be slidably matched of the sliding block 40 with slide rail 20 of lifting platform 30 is moved up and down, and is contained
Road aircraft is fixed on lifting platform 30, drives duct aircraft to move up and down regulation by lifting platform 30, to meet experiment
It is required that.Specifically, as shown in figure 3, in the present embodiment, lifting platform 30 comprising left cross bar 31, right cross bar 33, front rail 35 and after
Cross bar 37, sliding block 40 is respectively arranged on left cross bar 31 and right cross bar 33, and left cross bar 31 and right cross bar 33 are slided by sliding block 40 and set
In on slide rail 20, front rail 35 and rear transverse rod 37 are across left cross bar 31 and right cross bar 33, and before front rail 35 and rear transverse rod 37 are in
Position-adjustable it is placed on left cross bar 31 and right cross bar 33 afterwards, for the different duct aircraft of dimensions, so as to expand
The use scope of big duct Aerospace vehicle test device 100 of the present utility model.
As shown in Figures 1 and 2, one end of force cell 50 is fixed on external stability frame 10, force cell 50
The other end is connected with lifting platform 30；Specifically, in the present embodiment, force cell 50 be connected to support rail 15 with
Between left cross bar 31 and between support rail 15 and right cross bar 33, to ensure the reliability of test.In order that obtaining test result more
Accurately, therefore in the present embodiment, force cell 50 is four and is respectively arranged handing-over in left cross bar 31 and support rail 15
Place and the junction of right cross bar 33 and support rail 15, but be not limited.
The utility model is described above in association with most preferred embodiment, but the utility model is not limited to the above and taken off
The embodiment shown, and the various modifications carried out according to essence of the present utility model, equivalent combinations should be covered.
Claims (7)
1. a kind of duct Aerospace vehicle test device, it is applicable to the thrust of duct aircraft and pneumatic tests, it is characterised in that
The duct Aerospace vehicle test device includes：
External stability frame；
The slide rail at the external stability frame opposite sides is arranged in along the above-below direction of the external stability frame；
For fix be provided with the duct aircraft and the lifting platform in the external stability frame, the lifting platform with
The sliding block that the slide rail coordinates, the lifting platform is under being slidably matched of the sliding block and slide rail on relatively described external stability frame
Lower movement；
Force cell, one end of the force cell is fixed on the external stability frame, the force cell it is another
One end is connected with the lifting platform；And
Computer, is electrically connected with the force cell, and the computer is according to the pressure surveyed of the force cell
Or pulling force and the thrust and pneumatic state that simulate the duct aircraft.
2. duct Aerospace vehicle test device according to claim 1, it is characterised in that the external stability frame includes solid
Framework, the bottom plate being placed at the bottom of the space framework and the support rail for being installed for the force cell, it is described
Bottom plate covers the opening of the bottom of the space framework, and the slide rail is located at the left and right sides of the space framework respectively, described
Lifting platform is located in the space framework, and the support rail saves land in height adjustable and is assembled in front and rear the two of the space framework
At side.
3. duct Aerospace vehicle test device according to claim 2, it is characterised in that the space framework includes 14 aluminium
12 head and the tail in alloy profile, 14 aluminium alloy extrusions are docked and structure goes out rectangular box, 14 aluminium alloy extrusions
In remainder 2 be respectively supported at the left and right sides of the rectangular box, the slide rail is respectively positioned at the rectangular box
The left and right sides, the support rail saves land in height adjustable and is assembled at the front and rear sides of the rectangular box.
4. duct Aerospace vehicle test device according to claim 3, it is characterised in that the surrounding tool of the aluminium alloy extrusions
There is the guide groove of indent.
5. duct Aerospace vehicle test device according to claim 2, it is characterised in that the lifting platform comprising left cross bar,
Right cross bar, front rail and rear transverse rod, the sliding block are respectively arranged on the left cross bar and right cross bar, the left cross bar and right horizontal stroke
Bar is slidedly arranged on the slide rail by the sliding block, and the front rail and rear transverse rod are described across the left cross bar and right cross bar
Force cell be connected between the support rail and the left cross bar and the support rail and the right cross bar it
Between.
6. duct Aerospace vehicle test device according to claim 5, it is characterised in that before the front rail and rear transverse rod are in
Position-adjustable it is placed on the left cross bar and right cross bar afterwards.
7. duct Aerospace vehicle test device according to claim 5, it is characterised in that the force cell be four and
It is respectively arranged the junction in the junction of the left cross bar and support rail and the right cross bar and support rail.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720054160.3U CN206466191U (en) | 2017-01-17 | 2017-01-17 | Duct Aerospace vehicle test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720054160.3U CN206466191U (en) | 2017-01-17 | 2017-01-17 | Duct Aerospace vehicle test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206466191U true CN206466191U (en) | 2017-09-05 |
Family
ID=59705149
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720054160.3U Expired - Fee Related CN206466191U (en) | 2017-01-17 | 2017-01-17 | Duct Aerospace vehicle test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206466191U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628249A (en) * | 2017-01-17 | 2017-05-10 | 深圳市哈威飞行科技有限公司 | Test device for duct aircraft and test method thereof |
| CN111746823A (en) * | 2020-07-06 | 2020-10-09 | 北京空间技术研制试验中心 | Test method for verifying ejection separation of cruise aircraft assembly |
| US10940917B2 (en) | 2016-09-12 | 2021-03-09 | Kai Concepts, LLC | Watercraft device with hydrofoil and electric propeller system |
| US10946939B1 (en) | 2020-04-22 | 2021-03-16 | Kai Concepts, LLC | Watercraft having a waterproof container and a waterproof electrical connector |
| US11485457B1 (en) | 2021-06-14 | 2022-11-01 | Kai Concepts, LLC | Hydrojet propulsion system |
| US11878775B2 (en) | 2021-07-13 | 2024-01-23 | Kai Concepts, LLC | Leash system and methods of use |
| US11897583B2 (en) | 2020-04-22 | 2024-02-13 | Kai Concepts, LLC | Watercraft device with hydrofoil and electric propulsion system |
-
2017
- 2017-01-17 CN CN201720054160.3U patent/CN206466191U/en not_active Expired - Fee Related
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10940917B2 (en) | 2016-09-12 | 2021-03-09 | Kai Concepts, LLC | Watercraft device with hydrofoil and electric propeller system |
| US11479324B2 (en) | 2016-09-12 | 2022-10-25 | Kai Concepts, LLP | Watercraft device with hydrofoil and electric propeller system |
| US11919608B2 (en) | 2016-09-12 | 2024-03-05 | Kai Concepts, LLC | Watercraft device with hydrofoil and electric propeller system |
| CN106628249A (en) * | 2017-01-17 | 2017-05-10 | 深圳市哈威飞行科技有限公司 | Test device for duct aircraft and test method thereof |
| CN106628249B (en) * | 2017-01-17 | 2023-08-15 | 深圳市哈威飞行科技有限公司 | Ducted aircraft testing device and testing method thereof |
| US10946939B1 (en) | 2020-04-22 | 2021-03-16 | Kai Concepts, LLC | Watercraft having a waterproof container and a waterproof electrical connector |
| US11091232B1 (en) | 2020-04-22 | 2021-08-17 | Kai Concepts, LLC | Watercraft having a waterproof container and a waterproof electrical connector |
| US11801919B2 (en) | 2020-04-22 | 2023-10-31 | Kai Concepts, LLC | Waterproof container having a waterproof electrical connector |
| US11897583B2 (en) | 2020-04-22 | 2024-02-13 | Kai Concepts, LLC | Watercraft device with hydrofoil and electric propulsion system |
| CN111746823A (en) * | 2020-07-06 | 2020-10-09 | 北京空间技术研制试验中心 | Test method for verifying ejection separation of cruise aircraft assembly |
| US11485457B1 (en) | 2021-06-14 | 2022-11-01 | Kai Concepts, LLC | Hydrojet propulsion system |
| US11878775B2 (en) | 2021-07-13 | 2024-01-23 | Kai Concepts, LLC | Leash system and methods of use |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| 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: 20170905 Termination date: 20220117 |