CN204731025U - Aviation piston engine inclined testing device - Google Patents
Aviation piston engine inclined testing device Download PDFInfo
- Publication number
- CN204731025U CN204731025U CN201520335407.XU CN201520335407U CN204731025U CN 204731025 U CN204731025 U CN 204731025U CN 201520335407 U CN201520335407 U CN 201520335407U CN 204731025 U CN204731025 U CN 204731025U
- Authority
- CN
- China
- Prior art keywords
- tilts
- engine
- turning axle
- worm
- mentioned
- 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
- 238000012360 testing method Methods 0.000 title claims abstract description 10
- 239000000203 mixture Substances 0.000 abstract 1
- 238000011156 evaluation Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 230000001050 lubricating effect Effects 0.000 description 2
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 2
- 239000010729 system oil Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Landscapes
- Testing Of Engines (AREA)
Abstract
The utility model discloses a kind of aviation piston engine inclined testing device, belong to air line technical field.This device primarily of the control gear that tilts, tilt forward and back the compositions such as control gear, obliquity sensor, torque sensor, TT&C system, computing machine.Wherein tilt control gear by turbine and worm Serve Motor Control, tilts forward and back control gear and controlled by servo electric jar.Obliquity sensor can measure the angle that engine tilts and tilts forward and back simultaneously, controller is by analyzing the angle of inclination of dip angle signal and the computer settings recorded, drived control turbine and worm servomotor and servo electric jar, control the angle of inclination that engine reaches computer settings.Torque sensor can measure the output torque of engine.
Description
Technical field
The utility model relates to a kind of aviation piston engine inclined testing device.Belong to air line technical field.
Technical background
The power system of current middle-size and small-size aircraft is based on aviation piston engine.The attitude of flight course medium power system is along with the attitudes vibration of aircraft.For ensureing that under various attitude power system all can steady operation, need carry out inclining experiment to power system, whether the work of evaluation power system oil supply system and lubricating system under regulation obliquity is normal, and whether engine power exports stablizes.Therefore, need a kind of aviation piston engine inclined testing device, aviation piston engine is evaluated.
Utility model content
The purpose of this utility model is a kind of aviation piston engine inclined testing device of design, inclining experiment is carried out to the power system of engine and aircraft, whether the work of evaluation power system oil supply system and lubricating system under regulation obliquity is normal, and whether engine power exports stablizes.
A kind of aviation piston engine inclined testing device, is characterized in that: by base, the forward and backward slant mechanism being installed on base, the pitching platform be installed on forward and backward slant mechanism, the mechanism that tilts be installed on pitching platform, be installed on the engine support tilted in mechanism and form; Wherein forward and backward slant mechanism comprises height adjustment bracket and servo-electric cylinder, is arranged side by side before and after both; Wherein height adjustment bracket upper end is by tilting forward and back turning axle and spring bearing is connected with above-mentioned pitching platform bottom surface, and lower end and the above-mentioned base of height adjustment bracket fix; Wherein the upper and lower end of servo-electric cylinder is connected with above-mentioned pitching platform and base respectively by oscillating bearing; The mechanism that wherein tilts comprises worm and gear servomotor and to tilt turning axle; Worm and gear servomotor is arranged on above-mentioned pitching platform by support member, and the turning axle that tilts is arranged on above-mentioned pitching platform by spring bearing; The turning axle first end that tilts is connected with worm and gear servomotor by reversing flange; Above-mentioned engine support is arranged on the second end of the turning axle that tilts, and engine body is arranged in engine support; Above-mentioned engine support is installed with for measuring "Left"-deviationist, Right deviation, leans forward, the obliquity sensor of hypsokinesis angle.
The method of work of described aviation piston engine inclined testing device, is characterized in that: rotated by the turbine and worm Serve Motor Control turning axle that tilts, thus control the angle that tilts of engine and speed; Control pitching platform by servo-electric cylinder to rotate around tilting forward and back turning axle, thus control angle that engine tilts forward and back and speed.
The beneficial effects of the utility model are:
(1), the utility model can control engine "Left"-deviationist, Right deviation, leans forward, the angle of hypsokinesis and speed, and is stabilized in predetermined angular;
(2), the utility model can measure the output torque of engine;
(3), the utility model can according to engine model and screw propeller model adjustment engine center height.
Accompanying drawing explanation
Below in conjunction with accompanying drawing and example, the utility model is described further.
Fig. 1 aviation piston engine inclined testing device one-piece construction figure;
Fig. 2 is system chart;
In figure: moment of torsion flange 101, spring bearing 102, the turning axle 103 that tilts, spring bearing 104, obliquity sensor 105, engine support 106, engine installing plate 107, engine body 108, screw propeller 109, pitching platform 110, spring bearing 111, tilt forward and back turning axle 112, height adjustment bracket 113, base 114, oscillating bearing 115, servo electric jar 116, oscillating bearing 117, turbine and worm servomotor 118.
Turbine and worm servomotor 118 is connected with the turning axle 103 that tilts by moment of torsion flange, and the base of servo electric jar is connected with pedestal by oscillating bearing, and output shaft is connected with pitching platform 110 by oscillating bearing.Obliquity sensor 105 is fixed on engine mounting bracket.Engine loading is master screw oar 109.Holder part selects height adjustment bracket 113.
Embodiment
Turbine and worm servomotor 117 is connected with the turning axle 103 that tilts by moment of torsion flange, can control angle that engine tilts and speed.Meanwhile, the output that moment of torsion flange can measure engine is turned round.The base of servo electric jar is connected with pedestal by oscillating bearing, output shaft is connected with pitching platform 110 by oscillating bearing, pitching platform 110 can be controlled rotate around tilting forward and back turning axle 112 by controlling servo electric jar output shaft telescopic, thus control angle that engine tilts forward and back and speed.
Obliquity sensor 105 is fixed on engine mounting bracket, can measure engine "Left"-deviationist, Right deviation simultaneously, lean forward, the angle of hypsokinesis.And real-time for the signal recorded can be transferred to controller.Controller, by analyzing the angle of inclination of dip angle signal and the computer settings recorded, drived control turbine and worm servomotor and servo electric jar, controls engine reaches computer settings angle of inclination with the speed of regulation.
Engine loading is master screw oar 109.Holder part selects height adjustment bracket 113, can according to engine model and screw propeller model adjustment engine center height.
Claims (1)
1. an aviation piston engine inclined testing device, is characterized in that:
By base (114), the forward and backward slant mechanism being installed on base (114), the pitching platform (110) be installed on forward and backward slant mechanism, the mechanism that tilts be installed on pitching platform (110), be installed on the engine support (106) tilted in mechanism and form;
Wherein forward and backward slant mechanism comprises height adjustment bracket (113) and servo-electric cylinder (116), is arranged side by side before and after both; Wherein height adjustment bracket (113) upper end is by tilting forward and back turning axle (112) and spring bearing is connected with above-mentioned pitching platform (110) bottom surface, and lower end and the above-mentioned base (114) of height adjustment bracket (113) fix; Wherein the upper and lower end of servo-electric cylinder (116) is connected with above-mentioned pitching platform (110) and base (114) respectively by oscillating bearing;
The mechanism that wherein tilts comprises worm and gear servomotor (118) and the turning axle that tilts (103); Worm and gear servomotor (118) is arranged on above-mentioned pitching platform (110) by support member, and the turning axle that tilts (103) is arranged on above-mentioned pitching platform (110) by spring bearing; Turning axle (103) first end that tilts is connected with worm and gear servomotor (118) by reversing flange (101);
Above-mentioned engine support (106) is arranged on the second end of the turning axle that tilts (103), and engine body (108) is arranged in engine support (106);
Above-mentioned engine support (106) is installed with for measuring "Left"-deviationist, Right deviation, leans forward, the obliquity sensor (105) of hypsokinesis angle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520335407.XU CN204731025U (en) | 2015-05-22 | 2015-05-22 | Aviation piston engine inclined testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520335407.XU CN204731025U (en) | 2015-05-22 | 2015-05-22 | Aviation piston engine inclined testing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204731025U true CN204731025U (en) | 2015-10-28 |
Family
ID=54389365
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520335407.XU Active CN204731025U (en) | 2015-05-22 | 2015-05-22 | Aviation piston engine inclined testing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204731025U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104880317A (en) * | 2015-05-22 | 2015-09-02 | 南京航空航天大学 | Aviation piston engine inclination test apparatus and operating method |
| CN107101833A (en) * | 2017-05-22 | 2017-08-29 | 浙江工业大学 | A kind of rotatable engine model mill ride |
-
2015
- 2015-05-22 CN CN201520335407.XU patent/CN204731025U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104880317A (en) * | 2015-05-22 | 2015-09-02 | 南京航空航天大学 | Aviation piston engine inclination test apparatus and operating method |
| CN107101833A (en) * | 2017-05-22 | 2017-08-29 | 浙江工业大学 | A kind of rotatable engine model mill ride |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20180282130A1 (en) | Systems and methods for slung load stabilization | |
| CN101810402B (en) | Real-time automatically leveled table and chair | |
| CN206856983U (en) | It is a kind of can be with the quadrotor of center-of-gravity regulating | |
| CN204731025U (en) | Aviation piston engine inclined testing device | |
| CN106882341B (en) | A kind of Self-Balancing vehicle device waterborne | |
| CN104880317A (en) | Aviation piston engine inclination test apparatus and operating method | |
| CN212556758U (en) | A balance adjustment device for load unmanned aerial vehicle | |
| CN110254652B (en) | Unmanned aerial vehicle retrieves charging device based on horizontal stable platform | |
| CN108964342B (en) | Semi-active inertial volume capable of continuously controlling inertial volume on line | |
| CN205719462U (en) | It is applied to the rolling of aviation fuel tank shake testing equipment | |
| CN103625642A (en) | Method of controlling the wing flaps and horizontal stabilizer of a hybrid helicopter | |
| CN106628167A (en) | Tilting mechanism for tilt rotor | |
| CN103057605A (en) | Height-and-inclination-angle-adjustable spoiler control device and control method thereof | |
| CN111942577A (en) | Gravity center balancing method of unmanned aerial vehicle and unmanned aerial vehicle | |
| CN104743107A (en) | Multi-rotor type aircraft | |
| CN104819822A (en) | Support system of hypersonic propulsion wind tunnel model | |
| CN105782678A (en) | Mechanical two-axis stability augmentation deck device for aerial survey of unmanned aerial vehicle | |
| JP2017514739A (en) | helicopter | |
| CN207190706U (en) | Mobile robot's height adaptive chassis | |
| CN106715262B (en) | Aircraft with hydraulic support columns between fuselage and wing | |
| CN114397905B (en) | Tilting transition wind tunnel flight experiment method and system of tilting rotorcraft | |
| CN202783791U (en) | Three-dimensional tripod head capable of being debugged | |
| CN116519210A (en) | Automatic measuring device and method for mass center of suspension type cruise ship | |
| CN105523172A (en) | Attack angle control system and attack angle control method | |
| CN211494448U (en) | Coaxial double-rotor unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20190618 Address after: 214000 Shengxiang, Yaxi Community, Luoshe Town, Huishan District, Wuxi City, Jiangsu Province Patentee after: Jiangsu Xin Yuan Aviation Technology Co., Ltd. Address before: No. 29, Qinhuai District, Qinhuai District, Nanjing, Jiangsu Patentee before: Nanjing University of Aeronautics and Astronautics |