CN203673266U - Steering engine hinge moment loading device - Google Patents
Steering engine hinge moment loading device Download PDFInfo
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- CN203673266U CN203673266U CN201320616489.6U CN201320616489U CN203673266U CN 203673266 U CN203673266 U CN 203673266U CN 201320616489 U CN201320616489 U CN 201320616489U CN 203673266 U CN203673266 U CN 203673266U
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- bearing seat
- tension
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- bearing
- pressure sensor
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- 238000012360 testing method Methods 0.000 abstract description 8
- 238000000034 method Methods 0.000 abstract description 5
- 230000008878 coupling Effects 0.000 description 12
- 238000010168 coupling process Methods 0.000 description 12
- 238000005859 coupling reaction Methods 0.000 description 12
- 238000007906 compression Methods 0.000 description 11
- 238000004088 simulation Methods 0.000 description 6
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 3
- 125000006850 spacer group Chemical group 0.000 description 3
- 210000004369 blood Anatomy 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002834 transmittance Methods 0.000 description 1
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Abstract
一种舵机铰链力矩加载装置，其特征是包括支架、底座、轴承座、拉压传感器，传感器承压座，加载作动杆，轴承，连接轴，作动电机；支架安装在底座上，作动电机固定在支架上方，电机与加载对象连接轴之间设置了S形拉压传感器，拉压传感器上端安装有承压座，下端使用连接螺栓与轴承座连接，连接轴一端连接到舵机，另一端连接轴承并与轴承座组合成一体，轴承座与拉压传感器为悬臂状态；试验时，舵机按飞行控制程序进行工作，加载装置按各弹道特征点的载荷通过控制程序驱动作动电机进行加载，载荷通过加载作动杆加载到承压座，经拉压传感器、轴承座、轴承、连接轴传递到舵机上，实现模拟舵机在飞行状态下的铰链力矩加载过程。
A steering gear hinge torque loading device is characterized in that it includes a bracket, a base, a bearing seat, a tension and pressure sensor, a pressure bearing seat for a sensor, a loading actuating rod, a bearing, a connecting shaft, and an actuating motor; The moving motor is fixed above the bracket, and an S-shaped tension and pressure sensor is installed between the motor and the connecting shaft of the loading object. The upper end of the tension and pressure sensor is equipped with a pressure seat, and the lower end is connected to the bearing seat with connecting bolts. One end of the connecting shaft is connected to the steering gear. The other end is connected to the bearing and combined with the bearing seat. The bearing seat and the tension and pressure sensor are in a cantilever state; during the test, the steering gear works according to the flight control program, and the loading device drives the actuating motor through the control program according to the load of each ballistic characteristic point Loading is carried out, the load is loaded to the pressure seat through the loading actuating rod, and is transmitted to the steering gear through the tension and pressure sensor, bearing seat, bearing, and connecting shaft, so as to realize the hinge moment loading process of the simulated steering gear in the flight state.
Description
Technical field
The utility model relates to flight control system Hardware-in-loop Simulation Experimentation, is specifically related to a kind of steering wheel hinge moment charger.
Background technology
The rudder face of aircraft is handled by steering wheel, and in the time of control surface deflection, the aerodynamic force that air-flow produces forms aerodynamic moment to rudderpost, and this moment is commonly referred to hinge moment.Hinge moment is very large on the impact of steering wheel, and its variation certainly will cause the variation of steering wheel dynamic perfromance, even destroys the characteristics of motion of steering wheel.Therefore in the time flying to control Hardware-in-loop Simulation Experimentation, steering wheel is carried out to hinge moment load test and be necessary.
It is generally the one test in steering wheel development process that steering wheel hinge moment loads, and not yet finds that relevant steering wheel hinge moment is loaded in flight control system semi-matter simulating system.
Utility model content
The utility model provides a kind of steering wheel hinge moment charger, the hinge moment loading problem to steering wheel while carrying out flight control system Hardware-in-loop Simulation Experimentation to solve.
A kind of steering wheel hinge moment charger, is characterized in that comprising support, base, bearing seat, tension-compression sensor, and sensor Pressure Block, loads operating bar, bearing, coupling shaft, start motor; Support is arranged on base, start motor is fixed on support top, between motor and loading object coupling shaft, be provided with S shape tension-compression sensor, tension-compression sensor upper end is provided with Pressure Block, lower end is used coupling bolt to be connected with bearing seat, coupling shaft one end is connected to steering wheel, and other end connection bearing is also combined into one with bearing seat, and bearing seat and tension-compression sensor are cantilever position; When test, steering wheel carries out work by flight control program, charger drives start motor to load by the load of each characteristic point of trajectory by control program, load is loaded into Pressure Block by loading operating bar, be delivered on steering wheel through tension-compression sensor, bearing seat, bearing, coupling shaft, realize the hinge moment loading procedure of simulation steering wheel under state of flight.
The utility model utilizes programme controlled start motor to load the steering wheel that flies to control Hardware-in-loop Simulation Experimentation, the load one of load and each characteristic point of trajectory to, can simulate more realistically the serviceability of steering wheel under state of flight, test findings is more reliable.
Accompanying drawing explanation
Fig. 1: a kind of steering wheel hinge moment of the utility model charger front elevation
Fig. 2: a kind of steering wheel hinge moment of the utility model charger side view
Embodiment:
Below in conjunction with accompanying drawing, the utility model is described further.
A kind of steering wheel hinge moment charger, as Fig. 1, shown in Fig. 2, comprise support 1, spacing fixture block 2, base 4, spacer pin 6, bearing seat 7, tension-compression sensor 9, sensor Pressure Block 10, load operating bar 11, bearing 12, coupling shaft 13, start motor 14, support 1 is arranged on base 4, start motor 14 is fixed on support 1 top, as shown in Figure 2, between motor and loading object coupling shaft 13, be provided with S shape tension-compression sensor 9, tension-compression sensor 9 upper ends are provided with Pressure Block 10, lower end is used coupling bolt 8 to be connected with bearing seat 7, coupling shaft 13 one end are connected to steering wheel, the other end is installed bearing 12 and is combined into one with bearing seat 7.So can realize steering wheel in loading hinge moment can rotate by testing requirements.After installing, bearing seat 7 is cantilever position with tension-compression sensor 9.Start motor 14 is load input source, the size of load is controlled by the control program of motor, the load of its input acts on Pressure Block 10 by the loading operating bar 11 on it, be delivered on bearing seat 7 through tension-compression sensor 9, in load transmittance process, pressure sensor 9 can measure the load data of start motor 14 true inputs, for checking the load that loading motor 14 is inputted, warranty test rigorous.
When steering wheel work drives coupling shaft 13 to rotate, likely make coupling shaft 13 cantilever end whippings.For avoiding this kind of situation, bearing seat 7 both sides mounting limit pins 6, by spacer pin 6 be arranged on spacing fixture block 2 on support 1 by the position limitation of bearing seat 7 in support 1, between spacer pin 6 and spacing fixture block 2, be clearance fit, while guaranteeing to load, bearing seat 7 can carry out certain displacement on loading direction.
While test, steering wheel carries out work by flight control program, and charger drives start motor 14 to load by the load of each characteristic point of trajectory by control program.Load is loaded into Pressure Block 10 by loading operating bar 11, is delivered on steering wheel through tension-compression sensor 9, bearing seat 7, bearing 12, coupling shaft 13, realizes the hinge moment loading procedure of simulation steering wheel under state of flight.
The just embodiment of this utility model that instructions is described, the various not fleshes and bloods to utility model that illustrate are construed as limiting, person of an ordinary skill in the technical field read after instructions can to before described embodiment make an amendment or be out of shape, and do not deviate from essence and the scope of utility model.
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320616489.6U CN203673266U (en) | 2013-09-30 | 2013-09-30 | Steering engine hinge moment loading device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320616489.6U CN203673266U (en) | 2013-09-30 | 2013-09-30 | Steering engine hinge moment loading device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203673266U true CN203673266U (en) | 2014-06-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320616489.6U Expired - Fee Related CN203673266U (en) | 2013-09-30 | 2013-09-30 | Steering engine hinge moment loading device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203673266U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104978489A (en) * | 2015-07-02 | 2015-10-14 | 北京航天自动控制研究所 | Minimum hinge moment pressing-down trajectory calculation method applicable to glide vehicle |
-
2013
- 2013-09-30 CN CN201320616489.6U patent/CN203673266U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104978489A (en) * | 2015-07-02 | 2015-10-14 | 北京航天自动控制研究所 | Minimum hinge moment pressing-down trajectory calculation method applicable to glide vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140625 Termination date: 20160930 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |