CN110109396B - Force arm adjusting and controlling device for airplane structural strength test - Google Patents
Force arm adjusting and controlling device for airplane structural strength test Download PDFInfo
- Publication number
- CN110109396B CN110109396B CN201910386633.3A CN201910386633A CN110109396B CN 110109396 B CN110109396 B CN 110109396B CN 201910386633 A CN201910386633 A CN 201910386633A CN 110109396 B CN110109396 B CN 110109396B
- Authority
- CN
- China
- Prior art keywords
- voltage
- module
- signal
- comparison
- display
- 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
Images
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
- G05B19/0423—Input/output
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/24—Pc safety
- G05B2219/24215—Scada supervisory control and data acquisition
Abstract
The invention provides a force arm adjusting and controlling device for an airplane structure strength test, belonging to the technical field of force arm control for the strength test; the device comprises a signal input module, a signal conversion module, a comparison voltage V1 module, a comparison voltage V2 module, a comparison circuit, a display module and a control loop for controlling the force arm motor, wherein one end of the signal conversion module is connected with the signal input module, the other end of the signal conversion module is connected with the input end of the comparison circuit, the comparison voltage V1 module and the comparison voltage V2 module are connected with the input end of the comparison circuit, and the output end of the comparison circuit is connected with the display module and the control loop; the invention solves the problem that the existing arm adjusting and controlling device can not be matched with a coordinated loading system for an airplane structure strength test, and the arm adjusting and controlling device can enable the arm adjusting and controlling process in the airplane structure strength test to be more visual and clear and realize the function of automatically adjusting the arm.
Description
Technical Field
The invention belongs to a moment arm adjusting and controlling device, and particularly relates to a moment arm adjusting and controlling device for an aircraft structural strength test.
Background
In the structural strength test of the airplane, some tests require the state of the arm adjusting device of the airplane to be controlled, and the specific requirements of the test require that the arm adjusting device is controlled to be in different states according to different test load spectrums, for example, the arm needs to be controlled to be in the states of a large arm (100 mm), a medium and large arm (80 mm), a medium arm (70 mm), a small arm (60 mm) and the like in some working conditions.
Because the existing testing machine is only provided with a telecommunication mechanism of the moment arm regulator and does not have corresponding control equipment, similar tests cannot be smoothly carried out, and other existing moment arm regulation control devices cannot be matched with a coordination loading system for an airplane structural strength test.
Disclosure of Invention
Aiming at the problems, the invention provides a force arm adjusting and controlling device for an aircraft structural strength test, which can complete the adjustment of an aircraft force arm by combining a coordinated loading control system, a motor and the like of the aircraft structural strength test so as to ensure the integrity and the high efficiency of the loading of the aircraft structural strength test.
The invention provides a force arm adjusting and controlling device which comprises a signal input module, a signal conversion module, a comparison voltage V1 module, a comparison voltage V2 module, a comparison circuit, a display module and a control loop for controlling a force arm motor, wherein one end of the signal conversion module is connected with the signal input module, the other end of the signal conversion module is connected with the input end of the comparison circuit, the comparison voltage V1 module and the comparison voltage V2 module are connected with the input end of the comparison circuit, and the output end of the comparison circuit is connected with the display module and the control loop.
Further, after the signal input module receives an input signal sent by a control device and the like, the signal conversion module converts the input signal into a variable voltage signal V, the comparison voltage V1 module and the comparison voltage V2 module provide a voltage V1, the voltage V2 and the variable voltage signal V to be compared in the comparison circuit respectively, after a corresponding comparison result signal is output to the display module, the display module outputs an optical signal to indicate that the moment arm should be reduced, the moment arm should be increased or the moment arm should be increased properly, the comparison result signal is also output to the control loop, and the motor of the moment arm is controlled by the control loop to perform corresponding increase or decrease operation of the moment arm.
Further, V1 and V2 provided by the comparison voltage V1 module and the comparison voltage V2 module can be set by a worker according to the requirement in advance, and V1> V2.
Furthermore, the comparison circuit is composed of a comparator and an inverter, and after the variable voltage signal V is compared with V1 and V2 respectively through the comparator, two groups of comparison signals are output and transmitted to the display module and the control loop through the inverter respectively.
Furthermore, the comparison voltage V1 module and the comparison voltage V2 module both comprise adjusting resistors, the comparator adopts an LM339 comparator, the comparison voltage V1 module and the comparison voltage V2 module are respectively connected to pins 7 and 4 of the comparator LM339, and a worker sets the voltage V1 and the voltage V2 by adjusting the resistors.
Further, the display module comprises two display module groups, the two display module groups are both provided with display signal lamps L1 and L2, the display signal lamp L1 and the display signal lamp L2 cannot be simultaneously lighted, and respectively represent 'increasing arm force' and 'reducing arm force'.
Furthermore, the two display module groups of the display module further include a power supply and transistors T3 and T4.
Further, the control loop includes high power switches T1 and T2 and a dc power source connected to T1 and T2.
Further, the display signal lamp L1 is connected to the comparison result signal output terminal of the V and V1 of the comparison circuit 5 through a transistor T3, and the display signal lamp L2 is connected to the comparison result signal output terminal of the V and V2 of the comparison circuit 5 through a transistor T4; the high-power switch T1 is connected with the comparison result signal output ends of V and V1 of the comparison circuit 5, and the high-power switch T2 is connected with the comparison result signal output ends of V and V2 of the comparison circuit 5.
Further, the inverter of the comparison circuit is a six-inverter 4069, and the high power switch of the control loop is IFR 250.
According to the design, when V is larger than V1, a display signal lamp L1 is lightened to show that the force arm is increased, and meanwhile, the motor rotates forwards to realize the increase of the force arm; when V is less than V2, a display signal lamp L2 lights to show that the force arm is reduced, and the motor rotates reversely to reduce the force arm; when V2< V < V1, the arm motor stops rotating, and the display signal lights L1 and L2 are not lighted.
The invention makes the force arm adjusting and controlling process in the airplane structure strength test more visual and clear, realizes the function of automatically adjusting the force arm, effectively improves the loading efficiency, and can be effectively combined with a coordinated loading control system, a motor and the like of the airplane structure strength test.
Drawings
FIG. 1 is a block diagram of the present invention;
in the figure: the display device comprises a signal input module, a signal conversion module 2, a comparison voltage V1 module 3, a comparison voltage V2 module 4, a comparison circuit 5, a display module 6, a display module 7 and a control loop 8.
Detailed Description
One specific embodiment of the invention is as follows: a moment arm adjusting and controlling device for an aircraft structure strength test comprises a signal input module 1, a signal conversion module 2, a comparison voltage V1 module 3, a comparison voltage V2 module 4, a comparison circuit 5, a display module 6 and a control loop 8. The end 1 of the signal input module is connected with a control device, and the end 8 of the control loop is connected with a control motor of the force arm. The servo control current signal in the control equipment is connected into the signal input module 1, and the input current signal is converted into a variable voltage signal V through a resistor Ri in the signal conversion module 2. The comparison circuit 5 comprises a comparator LM339 and a six-phase inverter (4069), wherein a valve voltage is respectively arranged at a pin 7 and a pin 4 of the comparator LM339, the comparison voltage V1 module 3 and the comparison voltage V2 module 4 are connected as shown in FIG. 1, the valve voltages of the pin 7 and the pin 4 of the LM339 can be changed into V1 and V2 by adjusting Rc of the comparison voltage, and V1> V2 is ensured. The display module 6 is formed by combining two display submodules, the two display submodules are provided with a 5V power supply, display signal lamps (L1 and L2) and triodes (T3 and T4), and the two display submodules are respectively connected with a V1 and V comparison end output end and a V2 and V comparison output end of the comparison circuit 5. The control circuit 8 comprises high-power switches T1 and T2, a binding post and a 27V direct-current power supply, wherein the high-power switch T1 is connected with a V and V1 comparison result signal output end of the comparison circuit 5, and the high-power switch T2 is connected with a V and V2 comparison result signal output end of the comparison circuit 5.
Another embodiment of the present invention is: a moment arm adjusting and controlling device for an aircraft structure strength test comprises a signal input module 1, a signal conversion module 2, a comparison voltage V1 module 3, a comparison voltage V2 module 4, a comparison circuit 5, a display module 6 and a control loop 8. The signal input module receives a control signal, and the control signal is converted into a variable voltage signal V by the signal conversion module 2. The comparison voltage V1 module 3 and the comparison voltage V2 module 4 can provide voltages V1 and V2 which are compared with the variable voltage signal V, and V1 and V2 are preset by a worker or a computer, can be set by adjusting a resistor, can also be set by replacing a power supply, but ensure that V1 is more than V2. The variable voltage V is compared with V1 and V2 in the comparator circuit, respectively. The comparison circuit comprises a comparator and four inverters (P1, P2, P3 and P4), wherein the comparator connects the comparison ends of the variable voltage V and V1 to the inverters P1 and P2 which are connected in parallel, and the comparator connects the comparison ends of the variable voltage V and V2 to the inverters P3 and P4 which are connected in parallel. The display module 6 comprises two display signal lamps (L1, L2), two triodes (T3, T4) and a power supply, wherein the display signal lamp L1 and the triode T3 are connected with the inverter P1 in series, the other end of the triode T3 is connected with the power supply, the display signal lamp L2 and the triode T4 are connected with the inverter P3 in series, and the other end of the triode T4 is connected with the power supply. The control circuit 8 comprises high-power switches T1 and T2, one end of a high-power switch T1 is connected with the inverter P2, one end of a high-power switch T2 is connected with the inverter P4, and the other ends of the two high-power switches T1 and T2 are connected with a direct-current power supply.
After the layout of the two embodiments, when the input signal V > V1, the U2 outputs a high level (i.e. 1), and the U1 outputs a low level (i.e. 0), so that the U3 outputs a high level (i.e. 1), the U4 outputs a low level (i.e. 0), and the high-power switch T1 is turned on. The +27V direct current voltage and the positive winding of the motor form a loop, and the motor rotates forwards to realize the increase of the force arm. Meanwhile, the U3 outputs high level (namely 1), the triode T3 is conducted, and the L1 is lightened, namely, the indicator lamp for increasing the moment arm is lightened. When V < V2, U1 outputs high level (namely 1), U2 outputs low level (namely 0), therefore, U4 outputs high level (namely 1), high-power switch tube T2 is conducted, and +27V direct current voltage forms a loop with the negative winding of the motor, the motor rotates reversely, and the moment arm is reduced. Meanwhile, the U4 outputs high level (namely 1), the triode T4 is conducted, and the L2 is lightened, namely, the indicator lamp for reducing the moment arm is lightened. When V2< V < V1, U1 and U2 output high level (namely 1), after reversing, the control signals of the high-power switching tubes T1 and T2 and the triodes T3 and T4 are all '0', so that T1 and T2 are cut off, and the arm motor stops rotating. T3, T4 is cut off, and the indicator light is not on. When no current signal i is input, the control loop does not work, namely the motor stops rotating.
Claims (7)
1. The utility model provides a arm of force regulation controlling means for aircraft structural strength is experimental, includes signal input module (1), signal conversion module (2), comparison voltage V1 module (3), comparison voltage V2 module (4), comparison circuit (5), display module (6) and control circuit (8) that are used for controlling the arm of force motor, its characterized in that: one end of the signal conversion module (2) is connected with the signal input module (1), the other end of the signal conversion module (2) is connected with the input end of the comparison circuit (5), the comparison voltage V1 module (3) and the comparison voltage V2 module (4) are connected with the input end of the comparison circuit (5), and the output end of the comparison circuit (5) is connected with the display module (6) and the control loop (8);
after the signal input module (1) receives a signal, the signal is converted into a variable voltage signal V by a signal conversion module (2), a comparison voltage V1 module (3) generates a voltage V1, a comparison voltage V2 module (4) generates a voltage V2, a voltage V1 and a voltage V2 are input into a comparison circuit (5) and are respectively compared with the variable voltage signal V, and corresponding comparison result signals are output to a display module (6) and a control loop (8);
the voltage V1> voltage V2;
the comparison circuit (5) is composed of a comparator and an inverter, after the variable voltage signal V is compared with the voltage V1 and the voltage V2 through the comparator, a plurality of groups of comparison signals are output to the inverter, and then the inverter transmits the inverted signals to the display module (6) and the control loop (8) respectively.
2. The moment arm adjusting and controlling device for the aircraft structural strength test is characterized in that: the comparator of the comparison circuit (5) is an LM339 comparator.
3. The moment arm adjusting and controlling device for the aircraft structural strength test is characterized in that: the comparison voltage V1 module (3) and the comparison voltage V2 module (4) both comprise adjusting resistors and are respectively connected to pins 7 and 4 of the comparator LM339, and a worker sets the voltage V1 and the voltage V2 through the adjusting resistors.
4. The moment arm adjusting and controlling device for the aircraft structural strength test is characterized in that: the display module (6) comprises two display module groups, the two display module groups are provided with display signal lamps L1 and L2, the display signal lamp L1 and the display signal lamp L2 cannot be simultaneously lighted, and the display signal lamps respectively show the increase of the moment arm and the reduction of the moment arm.
5. The moment arm adjusting and controlling device for the aircraft structural strength test is characterized in that: the two display module groups respectively comprise a power supply and triodes T3 and T4.
6. The moment arm adjusting and controlling device for the aircraft structural strength test is characterized in that: the control loop (8) comprises high-power switches T1 and T2 and a direct current power supply connected with T1 and T2.
7. The moment arm adjusting and controlling device for the aircraft structural strength test is characterized in that: the display signal lamp L1 receives a comparison result signal of a variable voltage signal V and a voltage V1 of the comparison circuit (5) through a triode T3, and the display signal lamp L2 receives a comparison result signal of the variable voltage signal V and a voltage V2 of the comparison circuit (5) through a triode T4; the high-power switch T1 receives the comparison result signal of the variable voltage signal V of the comparison circuit (5) and the voltage V1, and the high-power switch T2 receives the comparison result signal of the variable voltage signal V of the comparison circuit (5) and the voltage V2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910386633.3A CN110109396B (en) | 2019-05-09 | 2019-05-09 | Force arm adjusting and controlling device for airplane structural strength test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910386633.3A CN110109396B (en) | 2019-05-09 | 2019-05-09 | Force arm adjusting and controlling device for airplane structural strength test |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110109396A CN110109396A (en) | 2019-08-09 |
| CN110109396B true CN110109396B (en) | 2022-05-17 |
Family
ID=67489142
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910386633.3A Active CN110109396B (en) | 2019-05-09 | 2019-05-09 | Force arm adjusting and controlling device for airplane structural strength test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110109396B (en) |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8044623B2 (en) * | 2007-07-03 | 2011-10-25 | Seiko Epson Corporation | Drive control circuit for electric motor |
| CN203482118U (en) * | 2013-09-25 | 2014-03-12 | 深圳市创晶辉精密塑胶模具有限公司 | Light modulation motor control system circuit |
| CN103810917B (en) * | 2014-01-25 | 2016-04-20 | 中国人民解放军空军航空大学军事仿真技术研究所 | A kind of arm-type torque-feedback regulating device of change of schoolaeroplane |
| CN105186952A (en) * | 2015-07-31 | 2015-12-23 | 芜湖真空科技有限公司 | Control system for stabilizing vacuum degree of vacuum chamber |
| CN106357177B (en) * | 2016-10-28 | 2018-07-06 | 吉林大学 | A kind of controllor for step-by-step motor |
-
2019
- 2019-05-09 CN CN201910386633.3A patent/CN110109396B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN110109396A (en) | 2019-08-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204695646U (en) | Multifunctional digital code pipe display brassboard | |
| CN110109396B (en) | Force arm adjusting and controlling device for airplane structural strength test | |
| CN216774742U (en) | IGBT drive circuit capable of being turned off in grading mode | |
| CN205546053U (en) | LED bluetooth intelligent control ware | |
| CN208724068U (en) | Back-light starting circuit | |
| CN102811524A (en) | LED lamp and control circuit thereof | |
| CN202679722U (en) | LED drive power supply | |
| CN203490883U (en) | Fault simulation device of current type transformer | |
| CN113380053A (en) | Three-way output control panel | |
| CN209070400U (en) | Wide scope positive or negative high voltage regulating circuit and voltage-regulating system | |
| CN106932676B (en) | Transformer substation comprehensive test system based on ZYNQ platform | |
| US9204515B2 (en) | Light source module, light source module driving circuit and driving method | |
| CN203366550U (en) | Switching-value-automatic-control practical-training device | |
| CN202998558U (en) | Driving device and lighting device comprising same | |
| CN207897185U (en) | A kind of pure LED light load for LED driver test | |
| CN211671026U (en) | Power indicator lamp circuit simultaneously suitable for alternating current power supply and direct current power supply | |
| CN109874201A (en) | A kind of two line lighting control systems | |
| CN220273660U (en) | Signal switching circuit | |
| CN215117797U (en) | Three-way output control panel | |
| CN203812034U (en) | Comprehensive training device for ship/vessel-used lighting system | |
| CN214412403U (en) | Power output channel expanding unit | |
| CN204360134U (en) | Opto-electronic conversion board | |
| CN219496923U (en) | Carrier rocket commutation mining and braiding unit test system | |
| CN215896258U (en) | Relay circuit, relay device, and terminal block | |
| CN210428116U (en) | Simulation teaching device for electrical control system of urban rail transit vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |