CN214373349U - Solid attitude/rail control engine thrust vector testing device - Google Patents
Solid attitude/rail control engine thrust vector testing device Download PDFInfo
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- CN214373349U CN214373349U CN202023059212.7U CN202023059212U CN214373349U CN 214373349 U CN214373349 U CN 214373349U CN 202023059212 U CN202023059212 U CN 202023059212U CN 214373349 U CN214373349 U CN 214373349U
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Abstract
The utility model relates to a solid appearance rail accuse engine thrust vector testing arrangement. The device comprises a bottom plate, a force sensor lower supporting plate, a six-component force sensor, a force sensor upper top plate, a calibration force source, a posture/rail control bell-shaped tray, a solid posture/rail control engine, a T-shaped screw, a thread leveling device, a rail control common calibration force source mounting platform, a posture/rail control common calibration force source mounting platform, a nitrogen cylinder, a one-way valve, a precision pressure gauge and a measurement and control acquisition device. The utility model discloses can calibrate respectively attitude control thrust vector and rail accuse thrust vector, also can calibrate simultaneously. The calibration force source adopts a pneumatic loading mode, is easy to control and has higher dynamic precision. The mutual interference between the constraints is small, and the measurement accuracy is improved; under the action of constraint, the rack has higher natural frequency, and the dynamic response characteristic of the engine in the working process is ensured; the operation is good, and the rack is easy to center, install and dismantle.
Description
Technical Field
The utility model relates to an engine test technical field, concretely relates to solid appearance rail accuse engine thrust vector testing arrangement.
Background
The solid attitude/orbit control engine has the functions of orbit changing and tail end attitude adjusting, and the performance of the solid attitude/orbit control engine directly influences whether accurate aiming and direct collision can be realized by the missile. With the development of the solid rocket engine technology, some engines adopt a thrust vector control device, and the accurate measurement of the thrust vector has important significance for the development and performance evaluation of the engines. The output of each spray pipe of the engine is a force vector, accurate propulsion is provided for the engine, the real force value is difficult to measure due to the low response frequency of the test platform, and under the action of the multiple spray pipes, the factors of mutual interference of the thrust vectors are difficult to screen and reject, the interference is large, and the test precision is low. Therefore, aiming at the technical bottleneck, the technical problem of accurate test of the thrust vector of the solid attitude/orbit control engine is solved by developing the research on the thrust vector test technology of the solid attitude/orbit control engine, constructing a thrust vector test system and developing in-situ calibration.
At present, a six-component model and a six-component test bed are commonly used at home and abroad, and the six-component thrust vector test bed consists of a fixed frame, a movable frame, 6 force measuring assemblies, an in-situ calibration device, a safety frame and a force bearing pier. The engine is arranged on the movable frame, and the movable frame is connected with the fixed frame through the force measuring assembly; the fixed frame is fixed on the bearing pier, is a reference platform of the whole test bed and bears the main thrust and 5 lateral forces transmitted by the fixed frame through 6 force measuring assemblies; 6 dynamometry subassemblies provide 6 restraints for respectively moving the frame: 1Z axis, 2Y axis and 3X axis for limiting 6 freedom degrees of the engine and measuring component force applied by the engine; the safety frame is used for protecting the sensor when the movable frame is subjected to abnormal external force; the in-situ calibration device is used for calibrating 6 sensors before an engine hot test so as to ensure the measurement accuracy. Based on the 6 component forces measured by the 6 sensors, 6 components (force components in 3 directions and moment components in 3 directions) of the engine thrust vector in the rectangular coordinate system can be obtained, and the engine thrust vector can be obtained by synthesizing the forces by using the rigid body balance principle.
The following problems exist in the measurement of the thrust vector by using the six-component force model and the six-component force test bed:
(1) solving problems of model equations
The six-component force model provides 3 force equations, 3 moment equations and 1 engine weight reduction formula, and 7 unknowns can be solved. However, the thrust vector measurement requires solving for 9 parameters: 3 thrust vector components, 3 moment components, engine weight and 2 barycentric position coordinates, the equation cannot be solved.
Therefore, the utility model discloses assume that the engine barycenter position changes on the engine center axis all the time, simplifies the equation, can obtain numerical value and solve. However, for large solid rocket engines, this assumption is not reasonable, and large measurement errors are caused. Since the attitude/orbit control engine measured by the scheme is small, the error brought by the assumption is small.
(2) Problem of coaxiality
In order to ensure the accuracy of main thrust measurement, the axis of the engine is strictly coaxial with the test bed thrust sensor in the installation process of the engine, so that the installation difficulty of the engine is increased.
(3) Problem of vibration of the stand
The conventional six-component test bed has low natural frequency, and the mechanical vibration of a rack system can be caused by the huge impact of the ignition moment of an engine, so that the oscillation amplitude of a lateral force curve is overlarge.
(4) Mutual interference problem between spray pipes
Under the action of multiple spray pipes, thrust vectors among the spray pipes are relatively large in mutual interference, and screening and rejecting are difficult.
Disclosure of Invention
The to-be-solved technical problem of the utility model
The utility model relates to a solid appearance/rail accuse engine thrust vector testing arrangement to realize the accurate measurement of appearance/rail accuse engine thrust vector, provide technical support for accurate guidance.
Technical scheme adopted for solving technical problem
A solid attitude/rail control engine thrust vector testing device comprises a bottom plate 1, a force sensor lower supporting plate 2, a six-component force sensor 3, a force sensor upper top plate 4, a calibration force source 5, an attitude/rail control bell-shaped tray 6, a solid attitude/rail control engine 7, a T-shaped screw 8, a thread leveling device 9, an adjusting nut 10, a rail control common calibration force source mounting platform 11, an attitude/rail control common calibration force source mounting platform 12, a nitrogen cylinder 13, a one-way valve 14, a precision pressure gauge 15 and a measurement and control acquisition device 16,
the six-component force sensor 3 is respectively positioned and fixed with the upper top plate 4 of the force sensor and the lower supporting plate 2 of the force sensor through positioning holes, and the lower supporting plate 2 of the force sensor is fixed on the bottom plate 1;
the T-shaped screw 8 is arranged in a positive hole position, penetrates through the rail control common calibration force source mounting platform 11 or the attitude/rail control common calibration force source mounting platform 12, penetrates through the bottom plate 1, is placed on the operating platform, and is screwed with the washer by a nut;
the upper top plate 4 of the force sensor is embedded in a circular groove below the attitude/rail control bell-shaped tray 6, and is positioned with the bell-shaped tray through a positioning hole of the upper top plate 4 of the force sensor and fastened through a bolt; the solid attitude/orbit control engine 7 is positioned in the center of the bell-shaped tray and is connected through a flange plate above the bell-shaped tray, so that the coaxiality of the engine and the bell-shaped tray is ensured;
the calibration force source 5 is arranged on a rail-controlled common calibration force source mounting platform 11 or an attitude/rail-controlled common calibration force source mounting platform 12, and the output end of the calibration force source is sequentially connected with a nitrogen cylinder 13, a one-way valve 14 and a precision pressure gauge 15;
and a standard sensor and a six-component sensor 3 in the calibration force source 5 are connected with a measurement and control acquisition device 16 and are connected with a power supply.
Further, the thread leveling device 9 adjusts and measures the levelness of the upper end surface of the attitude/rail control bell-shaped tray 6, and the levelness of the device is ensured.
Further, the T-shaped screw 8 penetrates through the bottom plate 1 and is placed on the operating platform, and the T-shaped screw 8 is screwed with the washer through the nut to ensure the stability of the bolt and the whole device, and the T-shaped screws are 8.
Further, after the calibration force source 5 and the engine nozzle are horizontally aligned, the adjusting nut 10 is screwed down to ensure the stability of the rail-controlled common calibration force source mounting platform 11 or the attitude/rail-controlled common calibration force source mounting platform 12.
Advantageous effects
The utility model discloses can calibrate respectively attitude control thrust vector and rail accuse thrust vector, also can calibrate simultaneously. The utility model discloses a calibration force source adopts pneumatic loaded mode, easily controls, and has higher dynamic precision. The mutual interference between the constraints is small, and the measurement accuracy is improved; under the action of constraint, the rack has higher natural frequency, and the dynamic response characteristic of the engine in the working process is ensured; the operation is good, and the rack is easy to center, install and dismantle.
Drawings
FIG. 1 is a solid attitude/orbital control engine thrust vector testing device;
wherein: (1) the device comprises a bottom plate, (2) a force sensor lower supporting plate, (3) a six-component force sensor, (4) a force sensor upper top plate, (5) a calibration force source, (6) an attitude/rail control bell-shaped tray, (7) a solid attitude/rail control engine, (8) a T-shaped screw, (9) a thread leveling device, (10) an adjusting nut, (11) a rail control common calibration force source mounting platform, (12) an attitude/rail control common calibration force source mounting platform, (13) a nitrogen cylinder, (14) a one-way valve, (15) a precision pressure gauge and (16) a measurement and control acquisition device.
Detailed Description
The present invention will be further described in detail with reference to the accompanying drawings 1 and the specific embodiments:
1) 8T-shaped screws 8 penetrate through the fixed bottom plate 1 and are placed on the operating platform, and nuts and washers are screwed tightly to ensure the stability of the bolts and the whole device;
2) connecting the lower supporting plate 2 of the force sensor with the bottom plate 1, and embedding the lower supporting plate of the force sensor with a boss of the lower supporting plate of the force sensor through a groove in the center of the bottom plate;
3) installing a six-component force sensor 3, and positioning the six-component force sensor 3 respectively with an upper top plate 4 of the force sensor and a lower supporting plate 2 of the force sensor through positioning holes and connecting and fixing the six-component force sensor with a stud;
4) the upper top plate 4 of the force sensor is embedded through a circular groove below the posture/rail control bell-shaped tray 6, and is positioned with the bell-shaped tray through a positioning hole of the upper top plate 4 of the force sensor and fastened through a bolt;
5) the levelness of the upper end surface of the posture/rail-controlled bell-shaped tray 6 is adjusted and measured through a thread leveling device 9, so that the levelness of the device is ensured;
6) the attitude/rail control engine model is positioned at the center of the bell-shaped tray and is connected through a flange plate above the bell-shaped tray, so that the coaxiality of the engine and the bell-shaped tray is ensured;
7) loading the mounting platform 11 of the rail control common calibration force source or the mounting platform 12 of the attitude/rail control common calibration force source and the T-shaped screw 8 to the alignment hole position; the upper and lower parts of the upper and lower parts are pre-fastened by adjusting nuts 10;
8) a calibration force source 5 is installed on a rail control common calibration force source installation platform 11 or a posture/rail control common calibration force source installation platform 12, the height is adjusted by using an adjusting nut 10, and after the calibration force source 5 and an engine spray pipe are kept horizontally aligned, the adjusting nut 10 is screwed down to ensure the stability of the rail control common calibration force source installation platform 11 or the posture/rail control common calibration force source installation platform 12;
9) a nitrogen cylinder 13, a one-way valve 14, a precision pressure gauge 15 and a calibration force source 5 are connected in sequence;
10) the standard sensor and the six-component sensor 3 in the calibration force source 5 are respectively connected with the measurement and control acquisition device 16 and are connected with a power supply.
In-situ calibration and testing:
taking the attitude control thrust static calibration range as 0N-50N and the attitude control static thrust calibration range as 0N-1000N as an example, respectively selecting 6 points of 0N, 10N, 20N, 30N, 40N and 50N and 6 points of 0N, 200N, 400N, 600N, 800N and 1000N as calibration points for the attitude control thrust and the rail control thrust, sequentially carrying out calibration measurement, sequentially unloading after reaching the maximum calibration point until reaching 0 point, repeating the process, and completing the calibration of 3 cycles; the dynamic calibration selects calibration points as maximum thrust values of 50N and 500N to sequentially carry out calibration measurement, when the calibration points are reached and a curve to be tested is stable, the electromagnetic valve in the calibration force source 5 is manually started to generate dynamic excitation, and dynamic thrust test and measurement are carried out. The method specifically comprises the following steps:
1) after the system is installed and debugged, starting the measurement and control acquisition device 16 to monitor the parameter curves of the standard sensor and the six-component force sensor 3 in the calibration force source, and leveling each channel;
2) during static calibration, a static calibration force source is adopted, the one-way valve 14 is opened, the nitrogen cylinder 13 supplies air to the calibration force source, the air inlet pressure is adjusted to a calibration point through the precision pressure gauge 15 to be loaded and unloaded step by step, and the measurement and control acquisition device 16 monitors the test parameters of the standard sensor and the six-component sensor 3 to complete the static calibration;
3) during dynamic calibration, a dynamic calibration force source is adopted, a one-way valve 14 is opened, air is supplied to the calibration force source through a nitrogen cylinder 13, the air inlet pressure is adjusted to a calibration point through a precision pressure gauge 15, at the moment, an electromagnetic valve in the dynamic calibration force source 5 is opened, the calibration force source generates step impact force, and the standard sensor and the six-component force sensor 3 respectively measure respective dynamic responses.
Aiming at the problems that the traditional 4 three-component piezoelectric sensors are distributed at four corners and have unstable numerical values and cannot be corrected due to charge leakage after long working time of the piezoelectric sensors, a single six-component sensor is adopted to replace a pressure sensor test platform on the premise that the dynamic response of the test platform can meet technical indexes, and a calibration equation is obtained through corresponding test points to obtain the output force value of the spray pipe.
In order to verify the effectiveness of the utility model, the simulation posture/rail control engine is placed on a thrust test platform to carry out in-situ calibration test verification, and the test data are shown in table 1.
Table 1 main thrust calibration test results data table
The nonlinearity is 0.45%, the delay is 0.67%, and the repeatability is 0.47%, so that the high-precision testing device is fully shown to have high testing precision, meet the testing technical requirements, and ensure the rationality and the feasibility of the device.
Claims (5)
1. The utility model provides a solid appearance/rail accuse engine thrust vector testing arrangement which characterized in that: comprises a bottom plate (1), a lower supporting plate (2) of a force sensor, a six-component force sensor (3), an upper top plate (4) of the force sensor, a calibration force source (5), a posture/rail control bell-shaped tray (6), a solid posture/rail control engine (7), a T-shaped screw (8), a thread leveling device (9), an adjusting nut (10), a rail control common calibration force source mounting platform (11), a posture/rail control common calibration force source mounting platform (12), a nitrogen cylinder (13), a one-way valve (14), a precision pressure gauge (15) and a measurement and control acquisition device (16),
the six-component force sensor (3) is respectively positioned and fixed with the upper top plate (4) of the force sensor and the lower supporting plate (2) of the force sensor through positioning holes, and the lower supporting plate (2) of the force sensor is fixed on the bottom plate (1);
the positive hole position of the T-shaped screw (8) penetrates through a rail control common calibration force source mounting platform (11) or an attitude/rail control common calibration force source mounting platform (12), penetrates through the bottom plate (1), is placed on the operating platform, and is screwed with a washer by a nut;
the upper top plate (4) of the force sensor is embedded in a circular groove below the posture/rail control bell-shaped tray (6), is positioned with the bell-shaped tray through a positioning hole of the upper top plate (4) of the force sensor and is fastened through a bolt; the solid attitude/orbit control engine (7) is arranged at the center of the bell-shaped tray and is connected through a flange plate above the bell-shaped tray, so that the coaxiality of the engine and the bell-shaped tray is ensured;
the calibration force source (5) is arranged on a rail-controlled common calibration force source mounting platform (11) or a posture/rail-controlled common calibration force source mounting platform (12), and the output end of the calibration force source is sequentially connected with a nitrogen cylinder (13), a one-way valve (14) and a precision pressure gauge (15);
and a standard sensor and a six-component sensor (3) in the calibration force source (5) are connected with a measurement and control acquisition device (16) and are connected with a power supply.
2. The solid attitude/orbit control engine thrust vector testing device according to claim 1, characterized in that: the thread leveling device (9) adjusts and measures the levelness of the upper end surface of the posture/rail control bell-shaped tray (6) to ensure the levelness of the device.
3. The solid attitude/orbit control engine thrust vector testing device according to claim 1, characterized in that: the T-shaped screw (8) penetrates through the bottom plate (1) to be placed on the operating platform and is screwed down by the nut and the washer so as to ensure the stability of the bolt and the whole device, and the T-shaped screws are 8.
4. The solid attitude/orbit control engine thrust vector testing device according to claim 1, characterized in that: after the calibration force source (5) and the engine spray pipe are kept in horizontal alignment, the adjusting nut (10) is screwed down to ensure the stability of the rail control common calibration force source mounting platform (11) or the attitude/rail control common calibration force source mounting platform (12).
5. The solid attitude/orbit control engine thrust vector testing device according to claim 1, characterized in that: the calibration force source (5) adopts a pneumatic loading mode, is easy to control and has higher dynamic precision.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202023059212.7U CN214373349U (en) | 2020-12-18 | 2020-12-18 | Solid attitude/rail control engine thrust vector testing device |
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| CN202023059212.7U CN214373349U (en) | 2020-12-18 | 2020-12-18 | Solid attitude/rail control engine thrust vector testing device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112611568A (en) * | 2020-12-18 | 2021-04-06 | 内蒙航天动力机械测试所 | Solid attitude/rail control engine thrust vector testing device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112611568A (en) * | 2020-12-18 | 2021-04-06 | 内蒙航天动力机械测试所 | Solid attitude/rail control engine thrust vector testing device |
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