CN208630875U - VTOL fixed-wing unmanned plane iron bird testing stand - Google Patents
VTOL fixed-wing unmanned plane iron bird testing stand Download PDFInfo
- Publication number
- CN208630875U CN208630875U CN201820989885.6U CN201820989885U CN208630875U CN 208630875 U CN208630875 U CN 208630875U CN 201820989885 U CN201820989885 U CN 201820989885U CN 208630875 U CN208630875 U CN 208630875U
- Authority
- CN
- China
- Prior art keywords
- unmanned plane
- testing stand
- rudder face
- gantry
- plane
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Abstract
The utility model belongs to aircraft flight control system test platform technical field, more particularly to a kind of VTOL fixed-wing unmanned plane iron bird testing stand, including rack, gantry plane, front-axle beam, rear wall and movable rudder face, the front-axle beam and rear wall are vertically installed in the front end of gantry plane along the course of gantry plane, and are connected to gantry plane by right angle connection sheet and cornual plate；The movable rudder face and front-axle beam are separately positioned on the two sides of rear wall, and the movable rudder face setting is being connected by a hinge in Hou Qiang；The movable rudder face is attached thereto by the steering engine for being set to rear wall by link mechanism；The rear end of the gantry plane controls steering engine and Vertical Dynamic simulating piece by the way that circuit control panel is arranged respectively, realizes simulation test along the lateral setting Vertical Dynamic simulating piece of gantry plane.The utility model measuring accuracy is high, and structure is simple, and connection type is safe and reliable, simple and easy, at low cost.
Description
Technical field
The utility model belongs to aircraft flight control system test platform technical field, more particularly to a kind of VTOL
Fixed-wing unmanned plane iron bird testing stand.
Background technique
Iron bird testing stand full name " flies draining and presses system integration test bench frame ", is aircraft system synthesis, optimization design, seaworthiness
It collects evidence and goes into operation, the essential Critical Experiments Facility of continuing airworthiness.It is enterprising in winged draining pressure system integration test bench frame
Capable test is exactly iron bird test.Iron bird experiment includes main flight control system communication interface inspection, elevator system test, rudder
The pilot projects such as system test, aileron system test, spoiler system test.
The winged control of iron bird testing stand, hydraulic, Landing Gear System mechanical mounting interface, department enclosure installation site, hydraulic tube
Road arrangement trend and mounting means are consistent with actual airplane, carry aircraft system research and development and verifying, aircraft multisystem synthesis are tested
The test missions such as the seaworthiness of card and flight control system, hydraulic system and Landing Gear System verifying, are the machine system integration, peace of taking a flight test
Entirely, take a flight test malfunction elimination, subsequent models improve etc. provide important leverage.
Current iron bird testing stand primarily directed to large aircraft and unmanned plane experimental provision, due to large aircraft and light
Type aircraft is designed in structure and steerable system has difference substantially.Existing iron bird testing stand is large aircraft, is not had
The iron bird testing stand of small drone.Since architectural difference is larger, need to design special iron bird test for small drone
Platform.
In addition, it is also necessary to be designed for the wing section in iron bird testing stand.
Utility model content
To solve the above problems, the utility model provides a kind of VTOL fixed-wing unmanned plane iron bird testing stand, the nothing
Man-machine iron bird test bed testing precision is high, and structure is simple, and connection type is safe and reliable.
To achieve the above object, the utility model uses following technical scheme:
The utility model provides a kind of VTOL fixed-wing unmanned plane iron bird testing stand, including rack, gantry plane, after
Wall and movable rudder face, the rear wall are vertically installed in gantry plane along the course of gantry plane；The movable rudder face passes through hinge
It is connected to rear wall.
It further, further include steering engine, the steering engine is set to rear wall, which is connected by link mechanism and movable rudder face
It connects.
Further, the movable rudder face includes the wing flap of front setting and the aileron of rear portion setting；The wing flap and pair
The wing and actual wing flap and aileron stiffnes s equivalent.
It further, further include front-axle beam, the front-axle beam is separately positioned on the two sides of rear wall, the front-axle beam edge with movable rudder face
The course of the gantry plane is vertically installed in gantry plane.
Further, wall and/or front-axle beam are connected to gantry plane by right angle connection sheet and cornual plate after described, wherein institute
It states and reinforced sheet is set between the right angle connection sheet of front-axle beam and cornual plate.
Further, the front-axle beam and rear wall are connected with each other by setting flaperon reinforced sheet.
It further, further include Vertical Dynamic simulating piece, which vertically sets along the transverse direction of gantry plane
It is placed in the rear end of the gantry plane, the front-axle beam and rear wall is arranged along the course of gantry plane in the front end of the gantry plane.
It further, further include circuit control panel, which connect with steering engine and Vertical Dynamic simulating piece respectively；
When simulating unmanned plane VTOL, Vertical Dynamic simulating piece works under the control of circuit control panel；
When simulating unmanned plane horizontal flight, the wing flap of the movable rudder face is by circuit control panel through steering engine and connecting rod machine
Structure is rotated down along the axis of hinge；The aileron of the movable rudder face is by circuit control panel through steering engine and link mechanism along hinge
Axis be rotated up and down.
Further, the material of the gantry plane use aluminium sheet, the gantry plane be equipped with for convenient for simulation installation,
Dismantle the fluting of steering engine.
Further, the material of the Vertical Dynamic simulating piece uses slot aluminium, is bolted with the gantry plane；
The stiffnes s equivalent of the rigidity of the Vertical Dynamic simulating piece and actual Vertical Dynamic device.
The utility model is to need to design the iron bird for being capable of fixing and simulating primary control surface for light-duty fixed-wing unmanned plane
Testing stand, mainly by test-bed, be mounted on being formed on rack by test system, coordinative experiments equipment, completed instead of aircraft
The test of flight control system.
Compared with the prior art, the utility model has the following advantages:
1, compared to the high complexity of large aircraft iron bird testing stand, Gao Chengben, the utility model provides miniature self-service
The iron bird testing stand of machine, measuring accuracy is high, and structure is simple, and connection type is safe and reliable, simple and easy, at low cost.
2, small drone wing simulating piece can be fixed on rack by the rack of the utility model.
3, the movable rudder face simulating piece of the utility model can replace true aircraft to complete flight control system test.
4, routinely compared to large aircraft iron bird testing stand function, the utility model can simultaneously hang down to unmanned plane
Straight landing and horizontal flight both modalities which are tested, and are separately implemented at Vertical Square by Vertical Dynamic simulating piece and movable rudder face
To the movement with horizontal direction, rationally, work efficiency is high for design, and measuring accuracy is high.
5, Front wing spar used by the utility model and rear wall are simulating piece, and all-body configuration is easy to process.
6, steering engine reinforcer used by the utility model is simulating piece, is installed on rear wall convenient for steering engine.
7, movable rudder face and Vertical Dynamic simulating piece provided by the utility model are the simulating piece of stiffnes s equivalent, so that surveying
The precision of examination is guaranteed.
8, the steering engine of the utility model is connected on rear wall by right angle connection sheet and cornual plate, and by link mechanism with can
Dynamic rudder face connection, the shaft of movable rudder face is connected by hinge rear wall, so that steering engine controls movable rudder face by link mechanism
Movement, it is structurally reasonable, it is high-efficient.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the utility model；
Fig. 2 is the structural schematic diagram that the utility model front-axle beam is connect with rack；
The structural schematic diagram that Fig. 3 connect for wall after the utility model with steering engine；
The structural schematic diagram that Fig. 4 connect for wall after the utility model with movable rudder face.
Specific embodiment
Technical solution in order to enable those skilled in the art to better understand the present invention, with reference to the accompanying drawing and specific embodiment party
The present invention will be described in detail for formula.In the drawings, for constituent element identically or comparably, identical label is marked.
It is below only preferred forms of the invention, the present invention is not limited in following the description.
As shown in FIG. 1, FIG. 1 is the structural schematic diagram of the utility model, the utility model provides a kind of VTOL and fixes
Wing unmanned plane iron bird testing stand, including rack 1, gantry plane 2, rear wall 4 and movable rudder face 5, the rear wall 4 is along gantry plane 2
Course be vertically installed in gantry plane 2, and gantry plane 2 is connected to by right angle connection sheet 6 and cornual plate 8；Movable rudder face 5 is logical
Cross and be hingedly connected at rear wall 4, when concrete application, hinge uses hinge 13, as shown in figure 4, Fig. 4 be the utility model Hou Qiang with can
The structural schematic diagram of dynamic rudder face connection.
Shown in Fig. 3, the structural schematic diagram that Fig. 3 connect for wall after the utility model with steering engine, further includes steering engine 12, steering engine 12
It is set to rear wall 4, which is connect by link mechanism 14 with movable rudder face 5, and movable rudder face 5 includes the wing flap of front setting
With the aileron of rear portion setting；Wing flap and aileron and actual wing flap and aileron stiffnes s equivalent.
As shown in Fig. 2, Fig. 2 is the structural schematic diagram that the utility model front-axle beam is connect with rack, it further include front-axle beam 3, front-axle beam 3
The two sides of rear wall 4 are separately positioned on movable rudder face 5, front-axle beam 3 is vertically installed in gantry plane 2 along the course of gantry plane 2, and
It is connected to gantry plane 2 by right angle connection sheet 6 and cornual plate 8, reinforced sheet 7 is set between right angle connection sheet 6 and cornual plate 8.
Front-axle beam 3 and rear wall 4 are connected with each other by setting flaperon reinforced sheet 9.
Front-axle beam 3 and rear wall 4 are rectangular configuration.
It further include Vertical Dynamic simulating piece 10, which is vertically installed in along the transverse direction of gantry plane 2
The rear end of gantry plane 2, the front end setting front-axle beam 3 and rear wall 4 of gantry plane 2.
It further include circuit control panel, which connect with steering engine 12 and Vertical Dynamic simulating piece 10 respectively；
When simulating unmanned plane VTOL, Vertical Dynamic simulating piece 10 works under the control of circuit control panel；
When simulating unmanned plane horizontal flight, the wing flap of movable rudder face 5 is by circuit control panel through steering engine 12 and connecting rod machine
Structure 14 is rotated down along the axis of hinge 13；The aileron of movable rudder face 5 is by circuit control panel through steering engine 12 and link mechanism 14
Axis along hinge 13 is rotated up and down.
Rack 1 is formed by overlapping using aluminum profile by angle section；The width of rack 1 determines by the distance of front-axle beam 3 to rear wall 4,
Movable rudder face 5 is avoided to interfere in actuating range with rack 1, the tip of the length of rack 1 and front-axle beam 3 to Vertical Dynamic simulating piece
10 distance determines that the height of rack 1 is determined by frame sections.
Gantry plane 2 is process using aluminium sheet, aluminium sheet setting fluting, convenient for simulation installation and removal steering engine.
The material of Vertical Dynamic simulating piece 10 uses slot aluminium, is bolted with gantry plane 2；Vertical Dynamic simulating piece
The stiffnes s equivalent of 10 rigidity and actual Vertical Dynamic device.
Embodiment
As shown in FIG. 1, FIG. 1 is the structural schematic diagram of the utility model, the front end of the present embodiment gantry plane 2 is set along course
Set front-axle beam 3 and rear wall 4；Vertical Dynamic simulating piece 10 is vertically installed in the rear end of gantry plane 2 along the transverse direction of gantry plane 2.Its
In, front-axle beam 3 and rear wall 4 in the design process, are designed as rectangular configuration, in order to process and assemble.
As shown in Fig. 2, Fig. 2 is the structural schematic diagram that the utility model front-axle beam is connect with rack, front-axle beam 3 is connected by right angle
Piece 6, reinforced sheet 7 and cornual plate 8 are connected in gantry plane 2, the upper end of 6 connection reinforcement piece 7 of right angle connection sheet, under reinforced sheet 7
The cornual plate 8 at end setting right angle is connect with gantry plane 2, and this connection type is simple and easy, and cost is extremely low.
As shown in figure 3, the structural schematic diagram that Fig. 3 connect for wall after the utility model with steering engine, steering engine 12 are set to rear wall 4
And it is connect by link mechanism 14 with movable rudder face 5.Steering engine 12 is connected on rear wall 4 by right angle connection sheet 6 and reinforced sheet 7；
Steering engine 12 is connect by link mechanism 14 with movable rudder face 5.
As shown in figure 4, the structural schematic diagram that Fig. 4 connect for wall after the utility model with movable rudder face, movable rudder face 5 pass through
Hinge 13 is connected to rear wall 4, rotates by axis of the shaft of hinge 13；Movable rudder face 5 includes that the wing flap of front setting and rear portion are set
The aileron set；Wing flap and aileron and actual wing flap and aileron stiffnes s equivalent.
Setting circuit control panel controls steering engine 12 and Vertical Dynamic simulating piece 10 respectively.
When test, circuit control panel drives movable rudder face 5 by controlling steering engine 12, meanwhile, circuit control panel can also be controlled
Vertical Dynamic simulating piece 10 processed:
When simulating unmanned plane VTOL, Vertical Dynamic simulating piece 10 works under the control of circuit control panel；
When simulating unmanned plane horizontal flight, the wing flap of the movable rudder face 5 through steering engine 12 and is connected by circuit control panel
Linkage 14 is rotated down along the axis of hinge 13；The aileron of the movable rudder face 5 through steering engine 12 and is connected by circuit control panel
Linkage 14 is rotated up and down along the axis of hinge 13.
In this way, simulation light-weight vertical landing fixed-wing unmanned plane is tested, wherein Front wing spar described in the utility model
3 and rear wall 4 be simulating piece, all-body configuration is easy to process；The right angle connection sheet 6 and reinforced sheet 7 are simulating piece, are convenient for steering engine 12
It is connected on rear wall 4；The movable rudder face 5 is the simulating piece of stiffnes s equivalent, the rigidity and reality of the Vertical Dynamic simulating piece 10
The stiffnes s equivalent of the Vertical Dynamic device on border, so that the precision of test is guaranteed.The utility model structure is simple, connection type
Securely and reliably, simple and easy, it is at low cost.
Principle that embodiment of above is intended to be merely illustrative of the present and the illustrative embodiments used, however this hair
It is bright to be not limited thereto.For those skilled in the art, in the feelings for not departing from spirit and substance of the present invention
Under condition, various changes and modifications can be made therein.These variations and modifications are also considered as protection scope of the present invention.
Claims (10)
1. a kind of VTOL fixed-wing unmanned plane iron bird testing stand, including rack (1), gantry plane (2), rear wall (4) and can
Dynamic rudder face (5), which is characterized in that wall (4) is vertically installed in gantry plane (2) along the course of gantry plane (2) after described；It is described
Movable rudder face (5) is connected by a hinge in Hou Qiang (4).
2. VTOL fixed-wing unmanned plane iron bird testing stand according to claim 1, which is characterized in that further include rudder
Machine, the steering engine are set to rear wall (4), which is connect by link mechanism with movable rudder face (5).
3. VTOL fixed-wing unmanned plane iron bird testing stand according to claim 1 or 2, which is characterized in that it is described can
Dynamic rudder face (5) include the wing flap of front setting and the aileron of rear portion setting；The wing flap and aileron and actual wing flap and aileron
Stiffnes s equivalent.
4. VTOL fixed-wing unmanned plane iron bird testing stand according to claim 1, which is characterized in that further include front-axle beam
(3), the front-axle beam (3) and movable rudder face (5) are separately positioned on the two sides of rear wall (4), and the front-axle beam (3) is along the gantry plane
(2) course is vertically installed in gantry plane (2).
5. VTOL fixed-wing unmanned plane iron bird testing stand according to claim 1 or 4, which is characterized in that after described
Wall (4) and/or front-axle beam (3) pass through right angle connection sheet (6) and cornual plate (8) is connected to gantry plane (2), wherein the front-axle beam (3)
Right angle connection sheet (6) and cornual plate (8) between be arranged reinforced sheet (7).
6. VTOL fixed-wing unmanned plane iron bird testing stand according to claim 4, which is characterized in that the front-axle beam
(3) it is connected with each other with rear wall (4) by setting flaperon reinforced sheet (9).
7. VTOL fixed-wing unmanned plane iron bird testing stand according to claim 4, which is characterized in that further include vertical
Power simulating piece (10), the Vertical Dynamic simulating piece (10) are vertically installed in the gantry plane along the transverse direction of gantry plane (2)
(2) front-axle beam (3) and rear wall (4) is arranged along the course of gantry plane (2) in the front end of rear end, the gantry plane (2).
8. VTOL fixed-wing unmanned plane iron bird testing stand according to claim 7, which is characterized in that further include circuit
Control panel, the circuit control panel are connect with steering engine and Vertical Dynamic simulating piece (10) respectively；
When simulating unmanned plane VTOL, Vertical Dynamic simulating piece (10) works under the control of circuit control panel；
When simulating unmanned plane horizontal flight, the wing flap of the movable rudder face (5) is by circuit control panel through steering engine and connecting rod machine
Structure is rotated down along the axis of hinge；The aileron of the movable rudder face (5) is by circuit control panel through steering engine and link mechanism edge
The axis of hinge is rotated up and down.
9. VTOL fixed-wing unmanned plane iron bird testing stand according to claim 8, which is characterized in that the rack is flat
The material in face (2) uses aluminium sheet, and the gantry plane (2) is equipped with for the fluting convenient for simulation installation, disassembly steering engine.
10. VTOL fixed-wing unmanned plane iron bird testing stand according to claim 7, which is characterized in that described vertical
The material of power simulating piece (10) uses slot aluminium, is bolted with the gantry plane (2)；The Vertical Dynamic simulating piece
(10) stiffnes s equivalent of rigidity and actual Vertical Dynamic device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820989885.6U CN208630875U (en) | 2018-06-26 | 2018-06-26 | VTOL fixed-wing unmanned plane iron bird testing stand |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820989885.6U CN208630875U (en) | 2018-06-26 | 2018-06-26 | VTOL fixed-wing unmanned plane iron bird testing stand |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208630875U true CN208630875U (en) | 2019-03-22 |
Family
ID=65734758
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820989885.6U Active CN208630875U (en) | 2018-06-26 | 2018-06-26 | VTOL fixed-wing unmanned plane iron bird testing stand |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208630875U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113650814A (en) * | 2021-09-17 | 2021-11-16 | 北京国电高科科技有限公司 | Convenient type protector |
-
2018
- 2018-06-26 CN CN201820989885.6U patent/CN208630875U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113650814A (en) * | 2021-09-17 | 2021-11-16 | 北京国电高科科技有限公司 | Convenient type protector |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN207360600U (en) | Unmanned plane battery grips mechanism action device | |
| CN101726401B (en) | Scale measuring device for pitching dynamic derivative experiment | |
| CN109515683B (en) | Deformable wing with variable chord length and curvature | |
| CN101850850B (en) | Layout method of central airframe digital assembly of big plane | |
| CN106143898A (en) | A kind of VTOL tilting rotor fixed wing airplane | |
| CN208109379U (en) | A kind of helicopter built-up pattern experimental rig | |
| CN103287587A (en) | Ground-based simulation flight test platform of plane capable vertical take-off and landing | |
| CN102390522B (en) | Flow guide blade grid for short-distance takeoff and landing of airplane | |
| CN206537487U (en) | A kind of aircraft of the variable wing of aerofoil profile and the application wing | |
| CN208630875U (en) | VTOL fixed-wing unmanned plane iron bird testing stand | |
| RU2607675C1 (en) | Large-sized aerodynamic model | |
| CN102589840A (en) | Vertical or short-distance takeoff and landing aircraft ground effect test system | |
| CN106275434B (en) | A kind of aircraft rescue unmanned plane | |
| CN208070050U (en) | A kind of driving of rudder face and rudder face angle measuring mechanism | |
| CN104216401A (en) | Operating force and corresponding displacement test device of multiple freedom degree side lever | |
| CN111624422A (en) | Spacecraft system electrical integration test method based on open platform | |
| CN207607664U (en) | A kind of experiment load and support bogusware | |
| CN210852998U (en) | Unmanned aerial vehicle fuselage assembly is with assembling foling frock | |
| CN217945557U (en) | Flight control semi-physical simulation test bed | |
| CN205300888U (en) | A test model for measuring rudder face hinge moment | |
| CN114735175A (en) | Wing rudder angle transformation structure of towing testing machine of underwater glider | |
| CN209467320U (en) | A kind of all-wing aircraft unmanned plane that can be vertically moved up or down | |
| CN208468182U (en) | A kind of aircraft control stick assembly ground joint-trial platform | |
| CN208842615U (en) | A kind of unmanned plane landing gear structure | |
| CN207712184U (en) | A kind of splicing station for coach compartment door skeleton and covering |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210722 Address after: 518000 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: 518000 Xuefu Road (south) and Baishi Road (east) intersection of Nanshan District, Shenzhen City, Guangdong Province, 6-13 floors, Block B, Shenzhen Software Industry Base Patentee before: SF TECHNOLOGY Co.,Ltd. |