CN111426490B - Steering engine torque dynamic loading device in full-elastic state and testing method - Google Patents
Steering engine torque dynamic loading device in full-elastic state and testing method Download PDFInfo
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- CN111426490B CN111426490B CN201911218030.9A CN201911218030A CN111426490B CN 111426490 B CN111426490 B CN 111426490B CN 201911218030 A CN201911218030 A CN 201911218030A CN 111426490 B CN111426490 B CN 111426490B
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- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a dynamic steering engine torque loading device in a full-elastic state and a testing method. The support is the ring carrier, and the last empty groove of avoiding of four rudder pieces that is equipped with of ring carrier, and the ring carrier cup joints in the body outer wall of bullet, is located to be equipped with holding screw between the adjacent rudder piece on the ring carrier, and the locating plate is cross, and the vertical direction of locating plate is equipped with the constant head tank, and the constant head tank cup joints on the rudder piece to through screw fixed connection, elastic component includes mount pad and spring leaf, and the mount pad is installed on the ring carrier, and the spring leaf is installed in the draw-in groove of mount pad. The device can simulate and test whether the torque of the steering engine meets the requirement in the full-missile state, and further test the matching performance of the air rudder and the missile; the device has reliable installation and fixing modes and has no damage to the projectile body.
Description
Technical Field
The invention belongs to the field of airborne weapon control systems and projectile body structures, and particularly relates to a steering engine torque dynamic loading device in a full projectile state and a testing method.
Background
The steering engine is an important execution component of the missile servo mechanism, and the pneumatic load dynamically changes along with different flight attitudes in the missile flight process. The steering engine load table is generally adopted to measure the output torque of the steering engine in the steering engine development process, but in the measurement process, the steering engine is a single component. After the full missile final assembly, the air rudder moves along with the steering engine after being installed, additional friction torque of the steering engine is increased to a certain degree, and meanwhile, the steering engine is not effectively verified whether the steering engine is matched with other systems and single machines on the missile under the condition of dynamic load or not. In the process of missile flight, disastrous consequences can be caused by mismatching of the dynamic performance of the steering engine with the missile under load conditions. Therefore, a steering engine torque dynamic loading device under the full-missile condition is needed to be designed, and the matching performance of all systems of the missile is further tested by simulating the dynamic load under the flight trajectory.
Disclosure of Invention
The invention provides a steering engine torque dynamic loading device in a full-missile state, which can effectively simulate dynamic loads acting on an air rudder under a flight trajectory so as to further test the matching performance among all systems of a missile under a load condition. The device has the characteristics of convenience in installation, adjustability of loads according to different trajectories, simplicity and convenience in clamping process, high dynamic response speed and high reliability.
The dynamic steering engine torque loading device in the full-elastic state comprises a support and a positioning plate, wherein the support is fixedly installed on the outer wall of an elastic body, the positioning plate is fixedly installed on a rudder piece of an air rudder, and an elastic assembly for simulating air load is arranged between the support and the positioning plate.
Furthermore, the support is an annular support, four rudder piece clearance grooves are formed in the annular support, the annular support is connected to the outer wall of the projectile body in a sleeved mode, and a set screw is arranged between adjacent rudder pieces on the annular support.
Furthermore, the locating plate is cross, the vertical direction of locating plate is equipped with the constant head tank, the constant head tank cup joints on the rudder piece to through screw fixed connection.
Furthermore, the elastic component comprises a mounting seat and a spring piece, the mounting seat is mounted on the annular support, and the spring piece is mounted in a clamping groove of the mounting seat.
Furthermore, two circular bulges are arranged on the positioning plate, and the bulges are in close contact with the spring piece of the elastic component.
A method for dynamically testing the torque of a steering engine in a full-elastic state comprises the following steps:
s1: selecting an elastic element, and testing and recording the corresponding torque of the elastic element in different deformation states;
s2: the annular support is fixedly arranged on the outer wall of the elastic body, the positioning plate is fixedly arranged on the rudder piece of the air rudder, the elastic element is arranged between the annular support and the positioning plate, and the moment corresponding to the deformation state of the elastic element is loaded on the air rudder in a dynamic state;
s3: the deflection angle value is input to the steering engine of the air rudder through the controller, so that the air rudder deflects, and the controller reads the actual deflection angle value or other parameters of the controller to judge whether the steering engine meets the design requirements.
Further, in step S1, the elastic element is a spring plate, and the elastic force of the spring plate is measured by an elastic force meter.
Further, the other parameters include a current value of the steering engine.
Furthermore, the elastic element is arranged between the annular support and the positioning plate through a detachable structure, so that the elastic element with different elastic coefficients can be conveniently replaced.
Furthermore, in step S3, an angle sensor for measuring an actual deflection angle value is provided on the air vane, and the angle sensor is electrically connected to the controller.
The steering engine torque dynamic loading device in the full-elastic state provided by the invention has the following advantages:
1. the device can simulate and test whether the torque of the steering engine meets the requirement in the full-missile state, and further test the matching performance of the air rudder and the missile;
2. the device is reliable in installation and fixing mode and has no damage to the projectile body;
3. the device has simple structure, is convenient to produce and manufacture, and reduces the detection cost in the full-elastic state;
4. the spring piece is simple to disassemble and replace, and the test device can adapt to the test of various scene states;
5. the detection method using the device provided by the invention is simple to operate and convenient to measure, and simulates the dynamic load acting on the air rudder under the flight trajectory so as to further test the matching performance among all systems of the missile.
Drawings
FIG. 1 is a schematic structural diagram of a steering engine torque dynamic loading device in a full-elastic state;
FIG. 2 is a schematic structural view of a single air rudder with a positioning plate and a spring assembly;
FIG. 3 is a schematic view showing a relative position of the air vane in a zero position state according to embodiment 3;
FIG. 4 is a schematic diagram showing the relative positions of the air vanes in embodiment 3 when they are rotated in the forward direction by a certain angle;
fig. 5 is a schematic diagram showing the relative position of the rudder in embodiment 3 when the rudder rotates in a negative direction by a certain angle.
Wherein: 1-support, 2-mounting seat, 3-spring piece, 4-set screw, 5-positioning plate, 6-elastomer, 7-air rudder, 8-protrusion, 9-annular support, 10-rudder piece, 11-elastic component, 12-positioning groove, 13-screw, 14-clamping groove, 15-clearance groove, 16-steering engine and 17-air rudder midplane.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
Example 1:
as shown in fig. 1 and 2, the dynamic steering engine torque loading device in the full-elastic state comprises a support and a positioning plate, wherein the support is fixedly mounted on the outer wall of an elastic body, the positioning plate is fixedly mounted on a rudder piece of an air rudder, and an elastic assembly for simulating air load is arranged between the support and the positioning plate.
In the embodiment, the support is an annular support, and four rudder piece clearance grooves are formed in the annular support, so that the rudder pieces of the air rudder cannot interfere with the annular support within a specified movement angle; the annular support is sleeved on the outer wall of the projectile body, and a set screw is arranged between adjacent rudder pieces on the annular support.
The positioning plate is cross-shaped, a positioning groove is arranged in the vertical direction of the positioning plate, the positioning groove is sleeved on the rudder piece and fixedly connected through a screw, and a threaded hole matched and fixed with the screw is formed in the positioning plate, so that the positioning plate rotates along with the air rudder;
the elastic component comprises a mounting seat and a spring piece, the mounting seat is mounted on the annular support, and the spring piece is mounted in a clamping groove of the mounting seat.
The positioning plate is provided with two circular bulges, and the bulges are in close contact with the spring pieces of the elastic components.
A method for dynamically testing the torque of a steering engine in a full-elastic state comprises the following steps:
s1: selecting an elastic element, and testing and recording the corresponding torque of the elastic element in different deformation states;
s2: the annular support is fixedly arranged on the outer wall of the elastic body, the positioning plate is fixedly arranged on the rudder piece of the air rudder, the elastic element is arranged between the annular support and the positioning plate, and the moment corresponding to the deformation state of the elastic element is loaded on the air rudder in a dynamic state;
s3: the deflection angle value is input to the steering engine of the air rudder through the controller, so that the air rudder deflects, and the controller reads the actual deflection angle value or other parameters of the controller to judge whether the steering engine meets the design requirements.
In step S1, the elastic element is a spring plate, and the elastic force of the spring plate is measured by an elastic force meter.
In the embodiment, the steering engine is a direct current motor, the controller is electrically connected with the steering engine, and whether the steering engine is overloaded or not is judged according to the current value in the test process.
The elastic element is arranged between the annular support and the positioning plate through a detachable structure, so that the elastic elements with different elastic coefficients can be replaced conveniently.
The spring leaf that the elastic element was stainless steel or 65Mn steel material, its thickness is 0.5-4mm, calculates the moment that different elastic element correspond at different deformation angles through the elastometer test earlier, cup joints the constant head tank of locating plate on the rudder piece of air vane, locks with the screw, and the locating plate selects the metal or nonmetal material that the quality is light, intensity is high, in this embodiment, selects engineering plastics, selects the aluminum alloy in another embodiment. The annular support is sleeved on the outer wall of the projectile body, the installation position of the annular support is adjusted, the protrusion on the positioning plate is in close contact with the spring piece, the distance between two symmetrical surfaces of the clearance groove on the annular support and the rudder piece is measured to be equal, and the contact position of the spring piece and the protrusion is ensured to be symmetrical relative to the middle plane of the air rudder. And locking the set screw to fix the annular support and the elastomer, and arranging a threaded hole matched with the set screw on the annular support.
The air rudder comprises a steering engine and a rudder piece, the rudder piece is installed on the inner wall of the elastic body and is mechanically connected with the steering engine, the steering engine is electrically connected with a controller, the deflection angle value is input to the steering engine of the air rudder through the controller, the rudder piece of the air rudder deflects immediately, the spring piece is pushed to move when the protrusion rotates, the spring piece generates a reaction force to the protrusion after elastic deformation, then a moment for preventing the air rudder from rotating is generated, and a pneumatic load is acted on the air rudder in a flight simulation process.
Example 2:
the dynamic steering engine torque loading device in the full-elastic state comprises a support and a positioning plate, wherein the support is fixedly installed on the outer wall of an elastic body, the positioning plate is fixedly installed on a rudder piece of an air rudder, and an elastic assembly for simulating air load is arranged between the support and the positioning plate.
In the embodiment, the support is an annular support, and four rudder piece clearance grooves are formed in the annular support, so that the rudder pieces of the air rudder cannot interfere with the annular support within a specified movement angle; the annular support is sleeved on the outer wall of the projectile body, and a set screw is arranged between adjacent rudder pieces on the annular support.
The positioning plate is two clamping plates with T-shaped structures, is connected into a cross shape through a fastening piece and further is fixed with the rudder sheet into a whole, so that the positioning plate rotates along with the air rudder;
the elastic component comprises a mounting seat and a spring piece, the mounting seat is mounted on the annular support, and the spring piece is mounted in a clamping groove of the mounting seat.
In another embodiment, the elastic component is an integrated structure made of a spring sheet and is detachably arranged on the annular bracket through a fastening screw.
The positioning plate is provided with two circular bulges, and the bulges are in close contact with the spring pieces of the elastic components.
In this embodiment, be equipped with angle sensor on the air rudder, angle sensor and steering wheel are connected with the controller electricity, through the steering wheel of controller input deflection angle value to air rudder, the rudder piece of air rudder takes place to deflect promptly, promotes the spring leaf motion when protruding rotates, and the spring leaf produces reaction force to the arch after the elastic deformation, and then produces the moment that prevents air rudder pivoted, and the simulation in-process is acted on pneumatic load on the air rudder. And feeding back an actual deflection angle value of the rudder piece through an angle sensor, and checking whether the steering engine can bear the loaded dynamic load or not and whether the steering engine meets the design requirement or not so as to further check the matching performance among all the systems of the missile.
Example 3:
the dynamic steering engine torque loading device in the full-elastic state comprises a support and a positioning plate, wherein the support is fixedly installed on the outer wall of an elastic body, the positioning plate is fixedly installed on a rudder blade of an air rudder, and an elastic assembly for simulating air load is arranged between the support and the positioning plate.
In the embodiment, the support is an annular support, and four rudder piece clearance grooves are formed in the annular support, so that the rudder pieces of the air rudder cannot interfere with the annular support within a specified movement angle; the annular support is sleeved on the outer wall of the projectile body, and a set screw is arranged between adjacent rudder pieces on the annular support.
The positioning plate is cross-shaped, a positioning groove is arranged in the vertical direction of the positioning plate, and the positioning groove is sleeved on the rudder and fixedly connected through a screw, so that the positioning plate rotates along with the air rudder;
the elastic component comprises a mounting seat and spring pieces, the mounting seat is mounted on the annular support, the spring pieces are mounted in clamping grooves of the mounting seat, different replaceable spring pieces are used for testing, fixing screws are further arranged on the clamping grooves, the spring pieces can be conveniently dismounted on the mounting seat, and meanwhile the mounting seat is connected with the spring pieces more firmly.
The positioning plate is provided with two circular bulges, and the bulges are in close contact with the spring pieces of the elastic components.
As shown in fig. 3, 4 and 5, during testing, the corresponding moments of the spring pieces in different deformation states are firstly tested and recorded, and then the positioning plate is sleeved on the spring pieces and fixed through screws; the annular support is sleeved on the elastic body, the spring piece is ensured to be in close contact with the protrusion, the distance between two symmetrical surfaces on the annular support and the air rudder is measured, the contact position of the spring piece and the protrusion is ensured to be symmetrical relative to the middle plane of the air rudder, and the fastening screw is locked to fix the annular support and the elastic body.
The deflection angle value is input to the steering engine of the air rudder through the controller, the rudder piece of the air rudder deflects, the spring piece is pushed to move when the protrusion rotates, the spring piece generates reaction force on the protrusion after elastic deformation, and then torque for preventing the air rudder from rotating is generated, pneumatic load acting on the air rudder is simulated in the flight process, wherein the steering engine can be comprehensively detected to detect whether the steering engine can bear loaded dynamic load or not through positive and negative rotation of the rudder piece, and whether the steering engine meets the design requirement or not is verified.
Claims (7)
1. The utility model provides a steering wheel moment developments loading device under full bullet state which characterized in that: the air rudder comprises a bracket and a positioning plate, wherein the bracket is fixedly arranged on the outer wall of an elastic body, the positioning plate is fixedly arranged on a rudder piece of the air rudder, and an elastic component for simulating air load is arranged between the bracket and the positioning plate;
the support is an annular support, four rudder piece clearance grooves are formed in the annular support, the annular support is sleeved on the outer wall of the projectile body, and a set screw is arranged between adjacent rudder pieces on the annular support;
the elastic assembly comprises a mounting seat and a spring piece, the mounting seat is mounted on the annular bracket, and the spring piece is mounted in a clamping groove of the mounting seat;
the positioning plate is provided with two circular bulges, and the bulges are in close contact with the spring pieces of the elastic components.
2. The steering engine torque dynamic loading device in the full-elastic state according to claim 1, characterized in that: the locating plate is cross, the vertical direction of locating plate is equipped with the constant head tank, the constant head tank cup joints on the rudder piece to through screw fixed connection.
3. A method for dynamically testing the torque of a steering engine in a full-elastic state by using the dynamic loading device of the steering engine in the full-elastic state as claimed in any one of claims 1-2 is characterized by comprising the following steps:
s1: selecting an elastic element, and testing and recording the corresponding torque of the elastic element in different deformation states;
s2: the annular support is fixedly arranged on the outer wall of the elastic body, the positioning plate is fixedly arranged on the rudder piece of the air rudder, the elastic element is arranged between the annular support and the positioning plate, and the torque corresponding to the deformation state of the elastic element is loaded on the rudder piece of the air rudder;
s3: the deflection angle value is input to the steering engine of the air rudder through the controller, so that the rudder piece of the air rudder deflects, and the controller reads the actual deflection angle value or other parameters of the rudder piece and judges whether the steering engine meets the design requirements or not.
4. The method for dynamically testing the torque of the steering engine in the full-elastic state according to claim 3, wherein the method comprises the following steps: in step S1, the elastic element is a spring plate, and the elastic force of the spring plate is measured by an elastic force meter.
5. The method for dynamically testing the torque of the steering engine in the full-elastic state according to claim 3, wherein the method comprises the following steps: the other parameters include the current value of the steering engine.
6. The method for dynamically testing the torque of the steering engine in the full-elastic state according to claim 3, wherein the method comprises the following steps: the elastic element is arranged between the annular support and the positioning plate through a detachable structure, so that the elastic elements with different elastic coefficients can be replaced conveniently.
7. The method for dynamically testing the torque of the steering engine in the full-elastic state according to claim 3, wherein the method comprises the following steps: in step S3, an angle sensor for measuring an actual deflection angle value is provided on the rudder blade of the air rudder, and the angle sensor is electrically connected to the controller.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911218030.9A CN111426490B (en) | 2019-12-03 | 2019-12-03 | Steering engine torque dynamic loading device in full-elastic state and testing method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911218030.9A CN111426490B (en) | 2019-12-03 | 2019-12-03 | Steering engine torque dynamic loading device in full-elastic state and testing method |
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| CN111426490A CN111426490A (en) | 2020-07-17 |
| CN111426490B true CN111426490B (en) | 2022-06-07 |
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| CN105632276A (en) * | 2016-02-26 | 2016-06-01 | 南京航空航天大学 | Rudder load simulator not generating surplus torque |
| CN205656450U (en) * | 2016-04-13 | 2016-10-19 | 上海优伟斯智能系统有限公司 | Steering wheel dynamic load loading emulation test device |
| CN206039173U (en) * | 2016-08-31 | 2017-03-22 | 中国兵器工业第二○三研究所 | A steering wheel corner measurement probe setting device for realizing semi -physical simulation |
| CN107121301A (en) * | 2017-06-02 | 2017-09-01 | 哈尔滨工业大学 | A kind of Loading for actuator demo system |
| CN107588972A (en) * | 2017-09-29 | 2018-01-16 | 兰州飞行控制有限责任公司 | A kind of Loading for actuator exerciser for simulating missile wing rudder face loading condition |
| CN207908178U (en) * | 2018-03-21 | 2018-09-25 | 江西东齐航空装备有限公司 | A kind of helicopter steering engine test system |
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2019
- 2019-12-03 CN CN201911218030.9A patent/CN111426490B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102288342A (en) * | 2011-05-17 | 2011-12-21 | 湖北航天技术研究院总体设计所 | Steering engine output torque and deflection angle measuring device |
| CN103499444A (en) * | 2013-10-24 | 2014-01-08 | 北京航空航天大学 | Actuator performance tester |
| CN104048840A (en) * | 2014-05-27 | 2014-09-17 | 湖北三江航天红峰控制有限公司 | Elastic load application device for steering engine |
| CN105632276A (en) * | 2016-02-26 | 2016-06-01 | 南京航空航天大学 | Rudder load simulator not generating surplus torque |
| CN205656450U (en) * | 2016-04-13 | 2016-10-19 | 上海优伟斯智能系统有限公司 | Steering wheel dynamic load loading emulation test device |
| CN206039173U (en) * | 2016-08-31 | 2017-03-22 | 中国兵器工业第二○三研究所 | A steering wheel corner measurement probe setting device for realizing semi -physical simulation |
| CN107121301A (en) * | 2017-06-02 | 2017-09-01 | 哈尔滨工业大学 | A kind of Loading for actuator demo system |
| CN107588972A (en) * | 2017-09-29 | 2018-01-16 | 兰州飞行控制有限责任公司 | A kind of Loading for actuator exerciser for simulating missile wing rudder face loading condition |
| CN207908178U (en) * | 2018-03-21 | 2018-09-25 | 江西东齐航空装备有限公司 | A kind of helicopter steering engine test system |
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