CN111735565A - Method and device for measuring thrust parameters of thrust engine - Google Patents
Method and device for measuring thrust parameters of thrust engine Download PDFInfo
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- CN111735565A CN111735565A CN202010288272.1A CN202010288272A CN111735565A CN 111735565 A CN111735565 A CN 111735565A CN 202010288272 A CN202010288272 A CN 202010288272A CN 111735565 A CN111735565 A CN 111735565A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/0028—Force sensors associated with force applying means
- G01L5/0038—Force sensors associated with force applying means applying a pushing force
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/16—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring several components of force
- G01L5/168—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring several components of force using counterbalancing forces
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
Abstract
The invention provides a method and a device for measuring thrust parameters of a thrust engine, which comprise the following steps: determining the component force of the thrust along the direction of the coordinate axis; calculating the thrust according to the component force of the thrust along the coordinate axis direction; calculating the moment of the thrust in the coordinate axis direction according to the moment balance; the moment of the thrust in the coordinate axis direction is decomposed to obtain a first moment and a second moment; calculating the component of the eccentricity in the coordinate axis direction by a least square method according to the first moment and the second moment; calculating the eccentricity and the eccentricity argument according to the component of the eccentricity in the coordinate axis direction; the first moment is parallel to the thrust, the second moment is perpendicular to the thrust, the component force of the thrust in the coordinate axis direction is obtained through calculation after being measured by M sensors, M is 3 or 4, the component force of the thrust in the coordinate axis direction can be determined after being measured by a small number of sensors, and parameters of the thrust are calculated through a least square method, so that the accuracy of thrust parameter measurement is improved, and the measurement precision is improved.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a method and a device for measuring thrust parameters of a thrust engine.
Background
At present, a thrust vector is taken as a key performance parameter of a rocket engine, and has important significance for controlling the operation attitude of an aircraft, improving the control precision and the like. When the specific impulse of the rocket engine is calculated, the thrust value measured by a ground test run is an important calculation parameter. The measurement result of the rocket engine thrust vector test system provides an important basis for evaluating the performance index of the engine. In addition, the test is the only method for evaluating the reliability and the service life of the engine, and is the only means for checking whether the engine is fixed or not and for checking and accepting. Therefore, rocket engine thrust vector testing systems have been the focus of the engine testing field.
The rocket engine thrust vector testing system comprises an axial thrust steady-state measuring system, an axial thrust dynamic measuring system, a thrust vector testing system and a thrust eccentricity measuring system. The thrust vector testing system comprises a horizontal type measuring system and a vertical type measuring system. The working principle of the thrust vector testing system is as follows: the engine is arranged on a thrust test platform by utilizing the rigid body balance principle, the freedom degree of the engine is limited by setting a proper constraint condition, 6 component forces under the constraint condition are obtained through measurement, then a force balance equation is solved for the 6 component forces, and finally the thrust parameter of the engine is obtained.
Under the constraint condition, 6 force components are obtained through the measurement of 6 force measurement assemblies, and because the number of the force measurement assemblies is large, the force measurement assemblies can interfere with each other, so that the measurement accuracy of the thrust vector test system is reduced. In addition, the method for solving the force balance equation for the 6 component forces can cause the computed thrust parameters to be inaccurate.
Disclosure of Invention
In view of the above, the present invention provides a method and an apparatus for measuring thrust parameters of a thrust engine, which can determine component force of thrust along a coordinate axis direction after measurement by a small number of sensors, and calculate parameters of the thrust by a least square method, thereby improving accuracy of thrust parameter measurement and improving measurement precision.
In a first aspect, an embodiment of the present invention provides a method for measuring a thrust parameter of a thrust engine, where the method includes:
determining the component force of the thrust along the direction of the coordinate axis;
calculating the thrust according to the component force of the thrust along the coordinate axis direction;
calculating the moment of the thrust in the coordinate axis direction according to the moment balance;
decomposing the moment of the thrust in the coordinate axis direction to obtain a first moment and a second moment;
calculating the component of the eccentricity in the coordinate axis direction by a least square method through the first moment and the second moment;
calculating the eccentricity and the eccentricity argument according to the component of the eccentricity in the coordinate axis direction;
the first moment is parallel to the thrust, the second moment is perpendicular to the thrust, the component force of the thrust along the coordinate axis direction is obtained through calculation after being measured by M sensors, and M is 3 or 4.
Further, the determining the component force of the thrust force along the coordinate axis direction includes:
obtaining axial component force of each force measuring point on the coordinate axis respectively;
and calculating the component force of the thrust along the coordinate axis direction according to the axial component force corresponding to each force measuring point on the coordinate axis.
Further, the method further comprises:
and calculating an included angle between the thrust and the coordinate axis according to the component force of the thrust along the coordinate axis direction.
Further, the calculating the eccentricity and the eccentricity argument according to the component of the eccentricity in the coordinate axis direction includes:
calculating the eccentricity and the eccentricity argument according to the following equations:
wherein rho is the eccentricity, phi is the eccentric amplitude, rhoxIs the component of the eccentricity in the x-axis direction, pyIs the component of the eccentricity in the y-axis direction.
In a second aspect, an embodiment of the present invention provides a thrust parameter measuring device for a thrust engine, the device including:
the determining unit is used for determining the component force of the thrust along the direction of the coordinate axis;
the thrust calculation unit is used for calculating the thrust according to the component force of the thrust along the coordinate axis direction;
the moment calculation unit is used for calculating the moment of the thrust in the coordinate axis direction according to the moment balance;
the decomposition unit is used for decomposing the moment of the thrust in the coordinate axis direction to obtain a first moment and a second moment;
an eccentricity component calculation unit, configured to calculate a component of the eccentricity in the coordinate axis direction by a least square method using the first moment and the second moment;
the eccentricity argument calculation unit is used for calculating the eccentricity and the eccentricity argument according to the component of the eccentricity in the coordinate axis direction;
the first moment is parallel to the thrust, the second moment is perpendicular to the thrust, the component force of the thrust along the coordinate axis direction is obtained through calculation after being measured by M sensors, and M is 3 or 4.
Further, the determining unit is specifically configured to:
obtaining axial component force of each force measuring point on the coordinate axis respectively;
and calculating the component force of the thrust along the coordinate axis direction according to the axial component force corresponding to each force measuring point on the coordinate axis.
Further, the apparatus further comprises:
and the included angle calculation unit is used for calculating the included angle between the thrust and the coordinate axis according to the component force of the thrust along the coordinate axis direction.
Further, the eccentricity argument calculation unit is specifically configured to:
calculating the eccentricity and the eccentricity argument according to the following equations:
wherein rho is the eccentricity, phi is the eccentric amplitude, rhoxIs the component of the eccentricity in the x-axis direction, pyIs the component of the eccentricity in the y-axis direction.
In a third aspect, an embodiment of the present invention provides an electronic device, including a memory and a processor, where the memory stores a computer program operable on the processor, and the processor implements the method described above when executing the computer program.
In a fourth aspect, embodiments of the invention provide a computer readable medium having non-volatile program code executable by a processor, the program code causing the processor to perform the method as described above.
The embodiment of the invention provides a method and a device for measuring thrust parameters of a thrust engine, wherein the method comprises the following steps: determining the component force of the thrust along the direction of the coordinate axis; calculating the thrust according to the component force of the thrust along the coordinate axis direction; calculating the moment of the thrust in the coordinate axis direction according to the moment balance; the moment of the thrust in the coordinate axis direction is decomposed to obtain a first moment and a second moment; calculating the component of the eccentricity in the coordinate axis direction by a least square method according to the first moment and the second moment; calculating the eccentricity and the eccentricity argument according to the component of the eccentricity in the coordinate axis direction; the first moment is parallel to the thrust, the second moment is perpendicular to the thrust, the component force of the thrust in the coordinate axis direction is obtained through calculation after being measured by M sensors, M is 3 or 4, the component force of the thrust in the coordinate axis direction can be determined after being measured by a small number of sensors, and parameters of the thrust are calculated through a least square method, so that the accuracy of thrust parameter measurement is improved, and the measurement precision is improved.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
In order to make the aforementioned and other objects, features and advantages of the present invention comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a flowchart of a thrust parameter measuring method of a thrust engine according to an embodiment of the present invention;
FIG. 2 is a schematic view of a thrust parameter measurement model of a thrust engine according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a sensor distribution structure according to an embodiment of the present invention;
fig. 4 is a schematic view of a thrust parameter measuring device of a thrust engine according to a second embodiment of the present invention;
fig. 5 is a schematic view of a thrust parameter measuring system of a thrust engine according to a third embodiment of the present invention;
FIG. 6 is a schematic view of a thrust parameter measurement system of another thrust engine provided in accordance with a third embodiment of the present invention;
fig. 7 is a schematic structural diagram of a base plate on which an axial pretension adjusting device is mounted according to a third embodiment of the present invention;
fig. 8 is a schematic view of another bottom plate structure provided in the third embodiment of the present invention;
fig. 9 is a schematic view of another bottom plate structure provided in the third embodiment of the present invention;
fig. 10 is a schematic structural diagram of an NOS-C904 six-component thrust sensor according to a third embodiment of the present invention;
fig. 11 is a schematic structural diagram of an axial pretension adjusting device according to a third embodiment of the present invention;
fig. 12 is a schematic view of an installation structure of a six-component thrust sensor according to a third embodiment of the present invention;
FIG. 13 is a schematic structural view of another axial pretension adjusting device according to a third embodiment of the present invention;
fig. 14 is a schematic structural view of a radial thrust measuring device provided in the third embodiment of the present invention;
FIG. 15 is a schematic structural view of another radial thrust measurement device provided in the third embodiment of the present invention;
fig. 16 is a schematic view of an installation structure of a test engine according to a third embodiment of the present invention;
fig. 17 is a schematic view of an installation structure of another test engine according to a third embodiment of the present invention.
Icon:
111-a determination unit; 112-a thrust calculation unit; 113-a torque calculation unit; 114-a decomposition unit; 115-eccentricity component calculation unit; 116-eccentricity argument calculation unit; 1-axial pre-tightening force adjusting device; 2-a radial thrust measurement device; 3-a bottom plate; 4-a groove; 5-inclined rib support plates; 6-vertical adapter plate; 7-nozzle force measuring adapter plate; 8-six component thrust sensor; 9-mounting bolts; 10-a gasket; 11-a spring plunger; 12-a head support seat; 13-a radial thrust sensor; 14-long nut; 15-universal shoe angle screw; 16-universal hoof corner support; 17-testing the engine; 18-inclined adapter plate.
Detailed Description
To make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
For the understanding of the present embodiment, the following detailed description will be given of the embodiment of the present invention.
The first embodiment is as follows:
fig. 1 is a flowchart of a thrust parameter measuring method of a thrust engine according to an embodiment of the present invention.
Referring to fig. 1, the method includes the steps of:
step S101, determining component force of thrust along the direction of a coordinate axis;
in this application, through sensor hoop evenly distributed measurement thrust size, the eccentricity and the eccentric argument of thrust, specifically refer to fig. 3, wherein, the quantity of sensor is 4, and the sensor is six component thrust sensor. When the thrust, the eccentricity and the eccentricity argument of the thrust are calculated, the test engine needs to be symmetrical in the initial period and the whole experimental process, the center of gravity is located on the Z axis, and the radial displacement of the center of gravity is ignored; the structural dimensions of the test engine are known and the mass and center of gravity change of the test engine can be calculated from the charge design, as well as the internal ballistic design. Simplifying the action of the thrust on the test bed into the action force passing through the origin O
Sum moment
Wherein, O is positioned at the center of a circle of the section of the head of the engine in the middle of the head supporting seat. The thrust parameter measurement model is described with reference to fig. 2. As shown in fig. 2, the X, Y and Z axes are cartesian coordinate axes. The Y-axis direction is the same as the gravity direction, and the Z-axis direction is the axial direction of the test engine, namely the thrust direction. Decomposing the gravity force W into a component W in the axial directionZAnd a component W in the radial directionY。
In addition, FX, FY and FZ are force components measured by each force measuring point in three directions; defining the eccentricity rho of the thrust as the distance from the center of mass C of the engine to the intersection point D of the thrust action line and the cross point C, which is perpendicular to the Z-axis section, and the eccentric argument phi of the thrust as the included angle between the eccentricity rho and the X-axis.
L is the distance between the plane of the 4 six-component thrust sensors and the plane of the O, and LWMeasuring the distance between the engine's center of gravity and the plane in which O is located, L, at a time point for each thrustYThe distance between the head radial thrust sensor and the symmetrical plane is d, and the diameter of the force measuring point distribution circle is d.
Step S102, calculating thrust according to the component force of the thrust along the coordinate axis direction;
specifically, the description is given with four force measurement points in terms of the balance of forces, with reference to equation (1):
wherein, FxComponent of thrust in the direction of the X-axis, Fx1Is the axial component of the first force measuring point in the X-axis direction, Fx2Is the axial component of the second force measuring point in the X-axis direction, Fx3Is the axial component of the third force measuring point in the X-axis direction, Fx4Is the axial component force of the fourth force measuring point in the X-axis direction, FyComponent of thrust in the direction of the Y-axis, Fy1Is the axial component force of the first force measuring point in the Y-axis direction, Fy2Is the axial component of the second force measuring point in the Y-axis direction, Fy3Is the axial component force of the third force measuring point in the Y-axis direction, Fy4Is the axial component force of the fourth force measuring point in the Y-axis direction, Fy5First radial thrust, F, acquired for a first radial sensory6Second radial thrust collected for a second radial sensor, W is the weight of the test engine, FzComponent of thrust in the Z-axis direction, Fz1Is the axial component force of the first force measuring point in the Z-axis direction, Fz2Is the axial component of the second force-measuring point in the Z-axis direction, Fz3Is the axial component force of the third force measuring point in the Z-axis direction, Fz4The axial component force of the fourth force measuring point in the Z-axis direction is shown, and F is the thrust force.
Formula (1) is the thrust obtained in the case of an axial pretension adjusting device formed by a vertical adapter plate, and the thrust obtained in the case of an axial pretension adjusting device formed by an inclined adapter plate is then referred to formula (2):
wherein, WYComponent of gravity in the radial direction, WZIs the component of gravity in the axial direction in the case of tilt.
Step S103, calculating the moment of the thrust in the coordinate axis direction according to the moment balance;
in particular, the resultant force F in the X-axis direction is based on moment balancexMoments Mxz and Mxy acting on the Z-axis and Y-axis, see equation (3):
wherein, Fx1Is the axial component of the first force measuring point in the X-axis direction, Fx2Is the axial component of the second force measuring point in the X-axis direction, Fx3Is the axial component of the third force measuring point in the X-axis direction, Fx4Is axial component force of a fourth force measuring point in the X-axis direction, d is the diameter of a force measuring point distribution circle, L is the distance between the plane of the 4 six-component thrust sensors and the plane of the O, and M isxzThe resultant force F in the X-axis directionxMoment acting on the Z axis, MxyThe resultant force F in the X-axis directionxMoment acting on the Y axis. Wherein the resultant force F in the X-axis directionxThe moments Mxz and Mxy acting on the Z axis and the Y axis are suitable for an axial pretightening force adjusting device formed by the vertical adapter plate and an axial pretightening force adjusting device formed by the inclined adapter plate.
Resultant force F in Y directionyThe moments Myx and Myz acting on the X and Z axes, with reference to equation (4):
wherein, Fy1Is the axial component force of the first force measuring point in the Y-axis direction, Fy2Is the axial component of the second force measuring point in the Y-axis direction, Fy3Is the axial component force of the third force measuring point in the Y-axis direction, Fy4Is the axial component force of the fourth force measuring point in the Y-axis direction, Fy5First radial thrust, F, acquired for a first radial sensory6Second radial thrust, W is the gravity of the test engine, L is the second radial thrust collected for the second radial sensorWMeasuring the distance between the engine's center of gravity and the plane in which O is located, M, at each thrust pointyxIs a resultant force F in the Y directionyMoment acting on the X axis, MyzIs a resultant force F in the Y directionyMoment acting on the Z axis. In addition, the formula (4) is suitable for the axial pretightening force adjusting device formed by the vertical adapter plate.
In the axial pretension force adjusting device formed by the inclined adapter plate, the resultant force F in the Y directionyThe moments Myx and Myz acting on the X and Z axes, with reference to equation (5):
wherein, WYIs the component of gravity in the radial direction.
Resultant force F in Z directionzMoments Mzx and Mzy acting on the X-axis and Y-axis, see equation (6):
wherein, Fz1Is the axial component force of the first force measuring point in the Z-axis direction, Fz2Is the axial component of the second force-measuring point in the Z-axis direction, Fz3Is the axial component force of the third force measuring point in the Z-axis direction, Fz4The axial component force of the fourth force measuring point in the Z-axis direction, d is the diameter of the distributed circle of the force measuring point, MzxIs a resultant force F in the Z directionzMoment acting on the X axis, MzyIs a resultant force F in the Z directionzMoment acting on the Y axis. In addition, resultant force F in the Z directionzThe moments Mzx and Mzy acting on the X and Y axes are suitable for the axial pretension adjusting device formed by the vertical adapter plate and the axial pretension adjusting device formed by the inclined adapter plate.
As described above, the moments Mx, My, Mz of the thrust acting on the X, Y, and Z axes can be obtained, referring to the formula (7):
wherein M isxFor moment of thrust acting on the X-axis, MyFor moment of thrust acting on the Y axis, MzThe moment acting on the Z axis is the thrust. In addition, the formula (7) is suitable for the axial pretightening force adjusting device formed by the vertical adapter plate.
In the axial pretension force adjusting device formed by the inclined adapter plate, the moments Mx, My and Mz of the thrust acting on the X axis, the Y axis and the Z axis refer to a formula (8):
wherein, WYIs the component of gravity in the radial direction.
Step S104, decomposing the moment of the thrust in the coordinate axis direction to obtain a first moment and a second moment;
in particular, the moment of the thrust
Split parallel to thrust
First moment of
And a second moment perpendicular to the thrust
Referring to formula (9):
wherein the content of the first and second substances,
unit vectors in the positive directions of the X, Y and Z axes, respectively.
In general
Only 10-4～10-6Of a certain order of magnitude, so can be approximated
For 0, referring to formula (10), the axial pretension force adjusting device formed by the vertical adapter plate is:
because the force, the mass center and the structure size in all directions are known, the unknown parameter to be solved in the equation set is only rhoxAnd ρyThus, the system of equations is an overdetermined system of equations.
In the axial pretightening force adjusting device formed by the inclined adapter plate, the overdetermined equation set refers to a formula (11):
step S105, calculating the component of the eccentricity in the coordinate axis direction by a least square method through the first moment and the second moment;
specifically, the over-determined equation set is solved by using the least square method, where the equation set GX ═ b is an over-determined equation set, that is, the number of rows of the corresponding coefficient matrix G is greater than the number of columns, and the least square solution X is obtained*Is a set of equations GTGX＝GTb solution of wherein GTIs a transposed matrix of G. This solution can minimize the 2-norm of the residual r-b-GX.
Step S106, calculating the eccentricity and the eccentricity argument according to the component of the eccentricity in the coordinate axis direction;
the first moment is parallel to the thrust, the second moment is perpendicular to the thrust, the component force of the thrust along the coordinate axis direction is obtained through calculation after being measured by M sensors, and M is 3 or 4.
Here, the sensor may be a six-component thrust sensor.
Further, step S101 includes the steps of:
step S201, obtaining axial component force corresponding to each force measurement point on a coordinate axis;
step S202, calculating the component force of the thrust along the coordinate axis direction according to the axial component force respectively corresponding to each force measuring point on the coordinate axis.
Further, the method further comprises:
and calculating the included angle between the thrust and the coordinate axis according to the component force of the thrust along the coordinate axis direction.
Further, step S106 includes:
calculating the eccentricity and eccentricity argument according to equation (12):
wherein rho is the eccentricity, phi is the eccentric amplitude, rhoxIs the component of eccentricity in the x-axis direction, pyIs the component of eccentricity in the y-axis direction.
The embodiment of the invention provides a method for measuring thrust parameters of a thrust engine, which comprises the following steps: determining the component force of the thrust along the direction of the coordinate axis; calculating the thrust according to the component force of the thrust along the coordinate axis direction; calculating the moment of the thrust in the coordinate axis direction according to the moment balance; the moment of the thrust in the coordinate axis direction is decomposed to obtain a first moment and a second moment; calculating the component of the eccentricity in the coordinate axis direction by a least square method according to the first moment and the second moment; calculating the eccentricity and the eccentricity argument according to the component of the eccentricity in the coordinate axis direction; the first moment is parallel to the thrust, the second moment is perpendicular to the thrust, the component force of the thrust in the coordinate axis direction is obtained through calculation after measurement of M sensors, M is 3 or 4, the component force of the thrust in the coordinate axis direction can be determined after measurement of a small number of sensors, and parameters of the thrust are calculated through a least square method, so that the accuracy of thrust parameter measurement is improved, and the measurement accuracy is improved.
Example two:
fig. 4 is a schematic view of a thrust parameter measuring device of a thrust engine according to a second embodiment of the present invention.
Referring to fig. 4, the apparatus includes:
a determination unit 111 configured to determine a component force of the thrust along the coordinate axis direction;
the thrust calculating unit 112 is used for calculating thrust according to the component force of the thrust along the coordinate axis direction;
the moment calculation unit 113 is used for calculating the moment of the thrust in the coordinate axis direction according to the moment balance;
the decomposition unit 114 is configured to decompose the moment of the thrust in the coordinate axis direction to obtain a first moment and a second moment;
an eccentricity component calculation unit 115 for calculating components of the eccentricity in the coordinate axis direction by a least square method using the first moment and the second moment;
an eccentricity argument calculation unit 116 for calculating an eccentricity and an eccentricity argument according to a component of the eccentricity in the coordinate axis direction;
the first moment is parallel to the thrust, the second moment is perpendicular to the thrust, component force of the thrust along the coordinate axis direction is obtained through calculation after measurement of M sensors, and M is 3 or 4.
Further, the determining unit 111 is specifically configured to:
obtaining axial component force corresponding to each force measuring point on a coordinate axis;
and calculating the component force of the thrust along the coordinate axis direction according to the axial component force corresponding to each force measuring point on the coordinate axis.
Further, the apparatus further comprises:
and an included angle calculation unit (not shown) for calculating an included angle between the thrust and the coordinate axis according to the component force of the thrust along the coordinate axis direction.
Further, the eccentricity argument calculation unit 116 is specifically configured to:
calculating the eccentricity and eccentricity argument according to equation (12):
wherein rho is the eccentricity, phi is the eccentric amplitude, rhoxIs the component of eccentricity in the x-axis direction, pyIs the component of eccentricity in the y-axis direction.
The embodiment of the invention provides a thrust parameter measuring device of a thrust engine, which comprises: determining the component force of the thrust along the direction of the coordinate axis; calculating the thrust according to the component force of the thrust along the coordinate axis direction; calculating the moment of the thrust in the coordinate axis direction according to the moment balance; the moment of the thrust in the coordinate axis direction is decomposed to obtain a first moment and a second moment; calculating the component of the eccentricity in the coordinate axis direction by a least square method according to the first moment and the second moment; calculating the eccentricity and the eccentricity argument according to the component of the eccentricity in the coordinate axis direction; the first moment is parallel to the thrust, the second moment is perpendicular to the thrust, the component force of the thrust in the coordinate axis direction is obtained through calculation after being measured by M sensors, M is 3 or 4, the component force of the thrust in the coordinate axis direction can be determined after being measured by a small number of sensors, and parameters of the thrust are calculated through a least square method, so that the accuracy of thrust parameter measurement is improved, and the measurement precision is improved.
Example three:
fig. 5 is a schematic view of a thrust parameter measurement system of a thrust engine according to a third embodiment of the present invention.
Referring to fig. 5, the system comprises an axial pretension adjusting device 1 and a radial thrust measuring device 2, wherein the axial pretension adjusting device 1 is used for adjusting axial pretension and measuring axial thrust, and the radial thrust measuring device 2 is used for measuring radial thrust. The vertical adapter plate in the axial pretightening force adjusting device 1 is vertically inserted into the groove of the bottom plate.
Fig. 6 is a schematic view of a thrust parameter measuring system of another thrust engine provided in the third embodiment of the present invention.
Referring to fig. 6, the system comprises an axial pretension adjusting device 1 and a radial thrust measuring device 2, wherein an inclined adapter plate in the axial pretension adjusting device 1 is obliquely inserted into a groove of a base plate. The system adopts the inclined adapter plate and the measuring form of the inclined proper angle, so that the fuel is in a downward flowing state and is not accumulated in a thrust chamber or other parts, and the faults of local overheating, burnthrough, even explosion and the like caused by accumulation of residual liquid propellant are avoided. Meanwhile, the angle adopted by the inclined adapter plate is appropriate, and the tail flame can not contact the ground aiming at the engine with small thrust and relatively small tail flame, so that the ablation or the scouring of the tail flame to the ground can be avoided.
The axial pretightening force adjusting device 1 comprises a plurality of sensors, a thrust parameter measuring device of the thrust engine is applied to the sensors, a single chip microcomputer is arranged in the sensors, and the thrust parameter is measured through the built-in single chip microcomputer. The acquired data can also be sent to a mobile phone or a computer through the sensor, and the measurement of the thrust parameter can be realized through the mobile phone or the computer.
Fig. 7 is a schematic structural diagram of a base plate on which an axial pretension adjusting device is mounted according to a third embodiment of the present invention.
Referring to fig. 7, when the axial pretension adjusting device formed by the vertical adapter plate is installed, the axial pretension adjusting device is inserted into the groove 4 of the base plate 3 and fixed by the screw and the inclined rib support plate 5, specifically referring to fig. 8. When the axial pretension adjusting device formed by the inclined adapter plate is installed, refer to fig. 9.
The axial pretightening force adjusting device can obtain real axial thrust of the engine by subtracting the pretightening force from the axial thrust measured by the sensor through accurately adjusting the pretightening force assembled by the sensor when axial thrust test is carried out, and the zero drift problem of thrust measurement can be simply eliminated by adopting the mode.
The axial pretightening force adjusting device adopts a six-component thrust sensor 8 (usually selecting an NOS-C904 six-component thrust sensor) with 4 annular uniformly distributed supports at the skirt part of the spray pipe, the sensor can simultaneously measure the force components in more than two directions, the appearance of the three-dimensional force sensor adopts a cylindrical flange structure, the top and the bottom of the sensor are the same in mounting surface and bolt pattern, the sensor is horizontal or vertical during mounting, one end of the flange is fixed through threads, and the other end of the flange is directly connected with a measured object, so that the measurement can be carried out. The NOS-C904 six-component thrust sensor is shown in FIG. 10.
2 unidirectional radial thrust sensors are adopted at a head supporting seat of the radial thrust measuring device, and the magnitude, the eccentricity and the eccentricity argument of the axial thrust can be calculated according to thrust values measured by the radial thrust sensors and the six-component thrust sensors.
The radial thrust measuring device adopts a horizontal measuring form, and the gravity only has a component in the direction vertical to the axis of the test engine, so that the gravity interference can be reduced, and the measurement of the thrust parameter is more accurate.
The axial pretension adjusting device comprises a vertical adapter plate 6, a nozzle force measuring adapter plate 7 and 4 six-component thrust sensors 8, see fig. 11.
The 4 six-component thrust sensors 8 are respectively matched with corresponding mounting bolts 9 and gaskets 10, and the mounting bolts 9 and the gaskets 10 can be used for adjusting pretightening force, refer to fig. 12. The compression amount of the spring is adjusted by adjusting the matched mounting bolt 9 and the spring plunger 11, so that the pre-tightening force with different sizes is adjusted.
The pre-tightening force adjusting mode of the spring plunger 11 is used, so that the accurate adjustment of the initial reading of the 4 six-component thrust sensors 8 is convenient to realize, and in the working process, the whole system is rigid, so that the system deformation is small, the compression amount change of the spring force is small, the spring force change is small, and the system measurement accuracy is high.
The 4 six-component thrust sensors 8 can be uniformly arranged on the vertical adapter plate and the nozzle force measuring adapter plate along the circumference. Before the engine is loaded and tested, the installation pretightening force of the spring plunger 11 is adjusted to exceed the zero drift range of the six-component thrust sensor 8, and the pretightening force measured by the 4 six-component thrust sensors 8 is kept consistent in the range which can be accurately measured and controlled by the sensors. After the pretightening force of each spring plunger 11 is adjusted, the thrust value is marked to be zero in the thrust parameter measuring system. In the actual experiment process under the state, when the axial thrust is measured, due to the action of the pre-tightening force, the measurement error caused by the zero drift of the axial force can be effectively avoided, and the operation is simple and convenient.
It should be noted that, evenly distributed has 8 sensor mounting holes on vertical keysets and spray tube keysets, and this application adopts 8 equipartitions of 4 six component thrust sensors to install, also can adopt 8 equipartitions of 3 six component thrust sensors to install. However, when a certain mounting hole has a problem and cannot be smoothly mounted, other mounting holes can be used, a mode that 4 six-component thrust sensors 8 are uniformly distributed and mounted is not necessarily adopted, and only a calculation method of thrust, eccentricity and eccentric amplitude angle is needed to be adjusted.
In addition, the axial pretension adjusting device further comprises an inclined adapter plate 18, a nozzle force measuring adapter plate 7 and 4 six-component thrust sensors 8, see fig. 13.
The 4 six-component thrust sensors 8 can be distributed uniformly on the inclined adapter plate 18 and the nozzle force-measuring adapter plate 7 along the circumference. After the experimental engine is loaded, because an inclination measurement mode is adopted, the gravity component of the engine along the axial direction of the engine can naturally serve as a partial pre-tightening force function, and the installation pre-tightening force of the spring plunger 11 is adjusted to a proper value to exceed the zero drift range of the axial thrust sensor, so that the zero drift range of the axial thrust sensor is within the range which can be accurately measured and controlled by the sensor, and the pre-tightening force measured by the 4 six-component thrust sensors 8 is ensured to be consistent.
Fig. 14 is a schematic structural diagram of a radial thrust measuring device according to a third embodiment of the present invention.
Referring to fig. 14, the radial thrust measuring device includes a head support 12, a radial thrust sensor 13, a long nut 14, a universal shoe angle screw 15, and a universal shoe angle support 16.
Because the dead weight effect of the test engine can be used as the pretightening force, the radial thrust measuring device does not need to debug the pretightening force, and only needs to be loaded before the experiment and then zeroed after the test engine, thereby avoiding the zero drift problem.
The head of test engine sets up on head supporting seat 12, and the arc shape of major diameter is adopted at the top of head supporting seat 12, can place the test engine of different diameter specifications. The two radial thrust sensors 13 are symmetrical to a symmetrical plane of the test engine perpendicular to the ground and are arranged below the head support base 12, so that the thrust data processing is facilitated.
The head support 12 and the radial thrust sensor 13 are supported by a universal shoe angle screw 15 and a universal shoe angle support 16, so that the angle and the direction of installation can be conveniently adjusted, and correction is also facilitated.
During the experiment, the angle can be adjusted to be vertical to the shaft of the test engine, so that the thrust value measured by the radial thrust sensor 13 is accurate. The universal shoe angle screw 15 and the universal shoe angle support base 16 can be easily adjusted in installation angle and direction, and refer to fig. 15 specifically.
Meanwhile, the universal hoof angle supporting seat 16 is arranged on the bottom plate in a movable state, and the two radial thrust sensors 13 are only acted in a direction perpendicular to the axis direction of the test engine, so that the calculation variables can be reduced, and the cost is saved.
Fig. 16 is a schematic view of an installation structure of a test engine according to a third embodiment of the present invention. Fig. 17 is a schematic view of an installation structure of another test engine according to a third embodiment of the present invention.
Referring to fig. 16 and 17, when the test engine 17 is installed, after the flange mounting hole at the test engine nozzle and the nozzle force measuring adapter plate are installed through bolts, the nozzle force measuring adapter plate and the test engine are integrated, and then the six-component thrust sensor and the matched bolts are installed on the vertical adapter plate.
Embodiments of the present invention further provide a computer readable medium having non-volatile program codes executable by a processor, where the computer readable medium stores a computer program, and the computer program is executed by the processor to perform the steps of the thrust parameter measurement method of the thrust engine of the above embodiments.
The computer program product provided in the embodiment of the present invention includes a computer-readable storage medium storing a program code, where instructions included in the program code may be used to execute the method described in the foregoing method embodiment, and specific implementation may refer to the method embodiment, which is not described herein again.
It is clear to those skilled in the art that, for convenience and brevity of description, the specific working processes of the system and the apparatus described above may refer to the corresponding processes in the foregoing method embodiments, and are not described herein again.
In addition, in the description of the embodiments of the present invention, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The functions, if implemented in the form of software functional units and sold or used as a stand-alone product, may be stored in a computer readable storage medium. Based on such understanding, the technical solution of the present invention may be embodied in the form of a software product, which is stored in a storage medium and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the embodiments of the present invention. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk or an optical disk, and other various media capable of storing program codes.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Finally, it should be noted that: the above-mentioned embodiments are only specific embodiments of the present invention, which are used for illustrating the technical solutions of the present invention and not for limiting the same, and the protection scope of the present invention is not limited thereto, although the present invention is described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: any person skilled in the art can modify or easily conceive the technical solutions described in the foregoing embodiments or equivalent substitutes for some technical features within the technical scope of the present disclosure; such modifications, changes or substitutions do not depart from the spirit and scope of the embodiments of the present invention, and they should be construed as being included therein. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (10)
1. A method of measuring a thrust parameter of a thrust engine, the method comprising:
determining the component force of the thrust along the direction of the coordinate axis;
calculating the thrust according to the component force of the thrust along the coordinate axis direction;
calculating the moment of the thrust in the coordinate axis direction according to the moment balance;
decomposing the moment of the thrust in the coordinate axis direction to obtain a first moment and a second moment;
calculating the component of the eccentricity in the coordinate axis direction by a least square method through the first moment and the second moment;
calculating the eccentricity and the eccentricity argument according to the component of the eccentricity in the coordinate axis direction;
the first moment is parallel to the thrust, the second moment is perpendicular to the thrust, the component force of the thrust along the coordinate axis direction is obtained through calculation after being measured by M sensors, and M is 3 or 4.
2. The method of measuring a thrust parameter of a thrust engine according to claim 1, wherein said determining a component force of the thrust force in the direction of the coordinate axis comprises:
obtaining axial component force of each force measuring point on the coordinate axis respectively;
and calculating the component force of the thrust along the coordinate axis direction according to the axial component force corresponding to each force measuring point on the coordinate axis.
3. The thrust parameter measurement method of a thrust engine according to claim 2, characterized in that it further comprises:
and calculating an included angle between the thrust and the coordinate axis according to the component force of the thrust along the coordinate axis direction.
4. The thrust parameter measurement method of a thrust engine according to claim 1, wherein said calculating the eccentricity and the eccentricity argument from the component of the eccentricity in the coordinate axis direction includes:
calculating the eccentricity and the eccentricity argument according to the following equations:
wherein rho is the eccentricity, phi is the eccentric amplitude, rhoxIs the component of the eccentricity in the x-axis direction, pyIs the component of the eccentricity in the y-axis direction.
5. A thrust parameter measuring device of a thrust engine, characterized in that the device comprises:
the determining unit is used for determining the component force of the thrust along the direction of the coordinate axis;
the thrust calculation unit is used for calculating the thrust according to the component force of the thrust along the coordinate axis direction;
the moment calculation unit is used for calculating the moment of the thrust in the coordinate axis direction according to the moment balance;
the decomposition unit is used for decomposing the moment of the thrust in the coordinate axis direction to obtain a first moment and a second moment;
an eccentricity component calculation unit, configured to calculate a component of the eccentricity in the coordinate axis direction by a least square method using the first moment and the second moment;
the eccentricity argument calculation unit is used for calculating the eccentricity and the eccentricity argument according to the component of the eccentricity in the coordinate axis direction;
the first moment is parallel to the thrust, the second moment is perpendicular to the thrust, the component force of the thrust along the coordinate axis direction is obtained through calculation after being measured by M sensors, and M is 3 or 4.
6. Thrust parameter measuring device of a thrust engine according to claim 5, characterized in that said determination unit is particularly adapted to:
obtaining axial component force of each force measuring point on the coordinate axis respectively;
and calculating the component force of the thrust along the coordinate axis direction according to the axial component force corresponding to each force measuring point on the coordinate axis.
7. The thrust parameter measurement device of a thrust engine according to claim 6, characterized in that said device further comprises:
and the included angle calculation unit is used for calculating the included angle between the thrust and the coordinate axis according to the component force of the thrust along the coordinate axis direction.
8. The thrust parameter measurement device of a thrust engine according to claim 5, wherein the eccentricity argument calculation unit is specifically configured to:
calculating the eccentricity and the eccentricity argument according to the following equations:
wherein rho is the eccentricity, phi is the eccentric amplitude, rhoxIs the component of the eccentricity in the x-axis direction, pyIs the component of the eccentricity in the y-axis direction.
9. An electronic device comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, wherein the processor implements the method of any of claims 1 to 4 when executing the computer program.
10. A computer-readable medium having non-volatile program code executable by a processor, wherein the program code causes the processor to perform the method of any of claims 1 to 4.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112696993A (en) * | 2020-11-04 | 2021-04-23 | 河北汉光重工有限责任公司 | Underwater rocket projectile thrust performance testing device |
| CN114636559A (en) * | 2022-04-06 | 2022-06-17 | 北京航空航天大学 | Radial thrust acquisition mechanism, thrust vector measurement device and method |
| CN114858334A (en) * | 2022-04-06 | 2022-08-05 | 北京航空航天大学 | Rocket engine thrust vector measuring device and thrust vector measuring method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104677543A (en) * | 2015-01-29 | 2015-06-03 | 重庆大学 | Piezoelectric type six-dimensional force/torque sensor adopting six groups of force-measuring sensitive units |
| CN108225776A (en) * | 2018-04-08 | 2018-06-29 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of small-size turbojet engine vector spray testboard |
| CN109084982A (en) * | 2018-08-29 | 2018-12-25 | 西安航天动力试验技术研究所 | A kind of high-thrust rocket three axis force measuring device and measuring method |
-
2020
- 2020-04-13 CN CN202010288272.1A patent/CN111735565A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104677543A (en) * | 2015-01-29 | 2015-06-03 | 重庆大学 | Piezoelectric type six-dimensional force/torque sensor adopting six groups of force-measuring sensitive units |
| CN108225776A (en) * | 2018-04-08 | 2018-06-29 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of small-size turbojet engine vector spray testboard |
| CN109084982A (en) * | 2018-08-29 | 2018-12-25 | 西安航天动力试验技术研究所 | A kind of high-thrust rocket three axis force measuring device and measuring method |
Non-Patent Citations (1)
| Title |
|---|
| 李贝: "发动机推力试车台推力测量分析及其特性仿真研究", 《中国优秀硕士学位论文全文数据库-工程科技Ⅱ辑》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112696993A (en) * | 2020-11-04 | 2021-04-23 | 河北汉光重工有限责任公司 | Underwater rocket projectile thrust performance testing device |
| CN112696993B (en) * | 2020-11-04 | 2022-07-29 | 河北汉光重工有限责任公司 | Underwater rocket projectile thrust performance testing device |
| CN114636559A (en) * | 2022-04-06 | 2022-06-17 | 北京航空航天大学 | Radial thrust acquisition mechanism, thrust vector measurement device and method |
| CN114858334A (en) * | 2022-04-06 | 2022-08-05 | 北京航空航天大学 | Rocket engine thrust vector measuring device and thrust vector measuring method |
| CN114636559B (en) * | 2022-04-06 | 2024-01-19 | 北京航空航天大学 | Radial thrust collection mechanism, thrust vector measurement device and method |
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