CN114858334A - Rocket engine thrust vector measuring device and thrust vector measuring method - Google Patents

Rocket engine thrust vector measuring device and thrust vector measuring method Download PDF

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Publication number
CN114858334A
CN114858334A CN202210354761.1A CN202210354761A CN114858334A CN 114858334 A CN114858334 A CN 114858334A CN 202210354761 A CN202210354761 A CN 202210354761A CN 114858334 A CN114858334 A CN 114858334A
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thrust
engine
force sensor
axial
axial force
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CN114858334B (en
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俞南嘉
周闯
蔡国飙
龚昊杰
师浩然
焦博威
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Beihang University
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Beihang University
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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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

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Abstract

The application relates to the technical field of aerospace, in particular to a rocket engine thrust vector measuring device and a rocket engine thrust vector measuring method. The rocket engine thrust vector measuring device comprises an axial thrust measuring module and a radial thrust measuring module; the axial thrust measurement module comprises a first support member, an axial force sensor, an adjustment member and a first transmission member; at least three axial force sensors are arranged; the radial thrust measuring module comprises a second support member, a radial force sensor, a second transmission member and a third support member; the number of radial force sensors is at least three. The thrust of the engine can be calculated according to the data of the axial force sensor and the radial force sensor; establishing a three-dimensional coordinate system by taking the center of the axial force sensor module as a coordinate origin, and calculating the moment of the thrust of the engine in the coordinate axis direction of the three-dimensional coordinate system; an equation set is established by utilizing moment balance, and the eccentricity argument of the thrust of the engine can be solved.

Description

Rocket engine thrust vector measuring device and thrust vector measuring method
Technical Field
The application relates to the technical field of aerospace, in particular to a rocket engine thrust vector measuring device and a rocket engine thrust vector measuring method.
Background
In the field of rocket engine thrust measurement, a common pull pressure sensor is commonly used for measurement at present, however, when the common pull pressure sensor is used for thrust measurement, the thrust value can only be measured simply, the thrust vector (such as thrust eccentricity) is difficult to measure, and the requirement of the rocket engine thrust measurement at present cannot be met.
Therefore, a rocket engine thrust vector measuring device is needed to solve the technical problems in the prior art to a certain extent.
Disclosure of Invention
The application aims to provide a rocket engine thrust vector measuring device and a rocket engine thrust vector measuring method, and the technical problems that only thrust numerical values can be measured and thrust vectors are difficult to measure when a common pull pressure sensor is used for thrust measurement in the prior art are solved to a certain extent.
The application provides a rocket engine thrust vector measuring device, which comprises an axial thrust measuring module and a radial thrust measuring module;
the axial thrust measurement module comprises a first support member, an axial force sensor, an adjustment member, and a first transmission member; the axial force sensor and the adjustment member are disposed between the first support member and the first transmission member for fixing a tail of an engine; the number of the axial force sensors is at least three, and the axial force sensors extend along the axial direction of the engine;
the radial thrust measurement module includes a second support member, a radial force sensor, a second transmission member, and a third support member; one end of the second transmission member is disposed on a third support member and the other end contacts a head of the engine, and one end of the radial force sensor is fixed to the third support member and the other end is disposed on the second support member; the number of the radial force sensors is at least three and extends in a radial direction of the engine.
In the above technical solution, further, the adjusting member includes a spring plunger; the ball end of the spring plunger abuts against the first support member, and the adjusting end of the spring plunger is arranged on the first transmission member;
the tensile force applied to the axial force sensor can be adjusted by adjusting the adjusting end of the spring plunger.
In the above technical solution, further, the number of the spring plungers is the same as the number of the axial force sensors, and the spring plungers and the axial force sensors are alternately arranged at equal intervals on the edge of the first transmission member.
In the above technical solution, further, the first transmission member includes a circular plate; the tail of the engine is fixed on the circular ring plate, and the engine is coaxial with the first circular ring plate.
In the above technical solution, further, the third support member includes a first ring; the second transmission component comprises a support rod, a pulley arranged at one end of the support rod and a first nut used for fixing the support rod on the first circular ring; the pulley is in contact with a head of the engine.
In the above technical solution, further, the device further comprises a support table; the first support component comprises a first support vertical plate and a support angle plate; the first supporting vertical plate is perpendicular to one end of the supporting platform, one end of the supporting angle plate is fixed on the supporting platform, and the other end of the supporting angle plate is fixed on the first supporting vertical plate;
the second support component comprises a second support vertical plate and a second circular ring arranged on the second support vertical plate; the second supporting vertical plate is perpendicular to the other end of the supporting platform.
In the above technical solution, further, a counter bore is formed in the second ring, one end of the radial force sensor is fixed to the first ring, and the other end of the radial force sensor passes through the counter bore and is fixed to the second ring through a second nut.
In the above technical solution, further, the number of the axial force sensors is four, and the number of the radial force sensors is three.
The application also provides a rocket engine thrust vector measuring method, which comprises the following steps of establishing a three-dimensional coordinate system and defining parameters;
calculating thrust of the engine from the readings of the axial force sensors and the readings of the radial force sensors;
calculating the moment of the thrust F of the engine in the coordinate axis direction according to the three-dimensional coordinate system;
and establishing an equation set by utilizing moment balance, and calculating the thrust eccentricity and the thrust eccentricity angle.
In the above technical solution, further, a three-dimensional coordinate system is established with the center of the first transmission member as an origin; defining the radial force sensor to be positive under the action of pressure, and respectively recording as F r1 、F r2 、F r3 A center distance of any of the radial force sensors to the third support member is r; defining the tensile force action of the axial force sensor as positive, respectively denoted as F z1 、F z2 、F z3 、F z4 A center distance d from any of the axial force sensors to the first transfer member; defining an axial distance LG between a center of mass of the engine and a center of a three-dimensional coordinate system, and defining an axial distance L between a center of the third support member and a center of a three-dimensional coordinate system r (ii) a Defining the thrust of the engine as F, and the thrust eccentricity P components of the engine are respectively P x 、P y The gravity of the engine is G;
by utilizing the force balance principle, three components F of the thrust F of the engine under a three-dimensional coordinate system x 、F y 、F z With the readings of the axial force sensor and the readings of the radial force sensor satisfying equation (1):
Figure BDA0003581943160000041
the thrust force F of the engine can be obtained according to the formula (1) and is shown as the formula (2):
Figure BDA0003581943160000042
the axial force sensor and the radial force sensor have moment in the x-axis direction in the three-dimensional coordinate system
Figure BDA0003581943160000043
Moments of the axial force sensor and the radial force sensor in the y-axis direction in the three-dimensional coordinate system
Figure BDA0003581943160000049
As shown in equation (3):
Figure BDA0003581943160000044
moment of thrust F of the engine in the x-axis direction in the three-dimensional coordinate system
Figure BDA0003581943160000045
Moment of thrust F of the engine in the y-axis direction in the three-dimensional coordinate system
Figure BDA0003581943160000046
As shown in equation (4):
Figure BDA0003581943160000047
the torque according to the thrust F of the engine is balanced with the torque of the axial force sensor and the torque of the radial force sensor, and the formula (5):
Figure BDA0003581943160000048
calculating a component P of a thrust eccentricity P of the engine from equations (3) to (5) x 、P y (ii) a Calculating a thrust eccentricity P of the engine and a thrust eccentricity argument phi of the engine by using a formula (6);
Figure BDA0003581943160000051
compared with the prior art, the beneficial effect of this application is:
the application provides a rocket engine thrust vector measuring device, which comprises an axial thrust measuring module and a radial thrust measuring module;
the axial thrust measurement module includes a first support member, an axial force sensor, an adjustment member, and a first transmission member; the axial force sensor and the adjustment member are disposed between the first support member and the first transmission member for fixing a tail of an engine; the number of the axial force sensors is at least three, and the axial force sensors extend along the axial direction of the engine;
the radial thrust measurement module includes a second support member, a radial force sensor, a second transmission member, and a third support member; one end of the second transmission member is disposed on a third support member and the other end contacts a head of the engine, and one end of the radial force sensor is fixed to the third support member and the other end is disposed on the second support member; the number of the radial force sensors is at least three and extends in a radial direction of the engine.
In conclusion, the thrust of the engine can be calculated according to the data of the axial force sensor and the radial force sensor; the method comprises the following steps of taking the center of an axial force sensor module as a coordinate origin and establishing a three-dimensional coordinate system, and calculating the moment of the thrust of an engine in the coordinate axis direction of the three-dimensional coordinate system; an equation set is established by utilizing moment balance, and the eccentricity argument of the thrust of the engine can be solved; further, by adopting the structure of the application, the thrust of the engine, the eccentricity and the eccentricity argument of the thrust of the engine can be measured by utilizing a common pull pressure sensor.
The application also provides a rocket engine thrust vector measurement method, which comprises the following steps:
establishing a three-dimensional coordinate system and defining parameters;
calculating thrust of the engine from the readings of the axial force sensors and the readings of the radial force sensors;
calculating the moment of the thrust F of the engine in the coordinate axis direction according to the three-dimensional coordinate system;
and establishing an equation set by utilizing moment balance, and calculating the thrust eccentricity and the thrust eccentricity angle.
Specifically, the rocket engine thrust vector measurement method provided by the application has the advantages of thrust numerical measurement and thrust eccentricity measurement. Meanwhile, the thrust numerical value measurement can be realized without using a radial thrust measurement module, and different thrust measurement occasions are considered.
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In order to more clearly illustrate the detailed description of the present application or the technical solutions in the prior art, the drawings needed to be used in the detailed description of the present application or the prior art description will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic overall structural diagram of a rocket engine thrust vector measuring device according to an embodiment of the present disclosure;
fig. 2 is a schematic structural diagram of an axial thrust measurement module in a rocket engine thrust vector measurement apparatus according to an embodiment of the present application;
FIG. 3 is a side view of an axial thrust measurement module in a rocket engine thrust vector measurement device according to an embodiment of the present disclosure;
fig. 4 is a schematic structural diagram of a radial thrust measurement module in a rocket engine thrust vector measurement apparatus according to an embodiment of the present application;
FIG. 5 is a side view of a radial thrust measurement module in a rocket engine thrust vector measurement device according to an embodiment of the present disclosure;
FIG. 6 is a schematic structural diagram of a first transmission member and an adjusting member in a rocket engine thrust vector measuring device according to an embodiment of the present application;
FIG. 7 is an enlarged view taken at A of FIG. 6;
fig. 8 is a schematic structural diagram of a rocket engine thrust vector measurement method according to a second embodiment of the present application.
Reference numerals:
100-axial thrust measurement module; 101-a radial thrust measurement module; 102-a first support member; 103-axial force sensor; 105-the adjustment end of the spring plunger; 106-a second support member; 107-radial force sensor; 108-a second transfer member; 110-the head of the engine; 111-the tail of the engine; 112-a spring plunger; 113-ball end of spring plunger; 114-a circular plate; 115-a first ring; 116-a support bar; 117-a pulley; 118-a first nut; 119-a support table; 120-a first support riser; 121-supporting gussets; 122-a second support riser; 123-a second ring; 124-counter bore; 125-second nut.
Detailed Description
The technical solutions of the present application will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are only some embodiments of the present application, but not all embodiments.
The components of the embodiments of the present application, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the present application, presented in the accompanying drawings, is not intended to limit the scope of the claimed application, but is merely representative of selected embodiments of the application.
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 application.
In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like 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, and 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 application. 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.
In the description of the present application, it should be noted that, unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, a fixed connection, a detachable 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 meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
Example one
Rocket engine thrust vector measurement apparatus according to some embodiments of the present application are described below with reference to fig. 1-7.
A rocket engine thrust vector measuring device comprises an axial thrust measuring module 100 and a radial thrust measuring module 101;
the axial thrust measurement module 100 comprises a first support member 102, an axial force sensor 103, an adjustment member and a first transmission member; the axial force sensor 103 and the adjusting member are arranged between the first supporting member 102 and the first transmission member, and the adjusting member can ensure that the axial force sensor 103 works in an accurate measuring range, so that the influence of zero drift of the axial force sensor 103 is eliminated; the first transmission member is used for fixing the tail part 111 of the engine, preferably, the tail part 111 of the engine is fixed to the first transmission member through eight M8 bolts, and the thrust of the engine is transmitted by the first transmission member and finally can be detected by the axial force sensor 103.
The radial thrust measuring module 101 includes a second support member 106, a radial force sensor 107, a second transmission member 108, and a third support member; one end of the second transmission member 108 is provided to a third support member and the other end contacts a head 110 of the engine, one end of the radial force sensor 107 is fixed to the third support member and the other end is provided to the second support member 106;
it is worth noting that: the number of the axial force sensors 103 is at least three, and the number of the radial force sensors 107 is at least three; ensuring the stability of the thrust of the engine detected by the axial force sensor 103 and the radial force sensor 107; the axial force sensor 103 extends in the axial direction of the engine; the radial force sensor 107 extends in the radial direction of the engine, i.e. the parameter of the thrust of the engine in the axial direction can be detected by the axial force sensor 103, and the parameter of the thrust of the engine in the radial direction can be detected by the radial force sensor 107.
In conclusion, the engine thrust can be calculated according to the data of the axial force sensor 103 and the radial force sensor 107; then, the center of the axial force sensor 103 module is used as a coordinate origin, a three-dimensional coordinate system is established, and the moment of the thrust of the engine in the coordinate axis direction of the three-dimensional coordinate system can be calculated; an equation set is established by utilizing moment balance, and the eccentricity argument of the thrust of the engine can be solved; further, by adopting the structure of the application, the thrust of the engine, the eccentricity and the eccentricity argument of the thrust of the engine can be measured by utilizing a common pull pressure sensor.
In this embodiment, shown in connection with fig. 1, 2 and 3, the adjustment member comprises a spring plunger 112 and the first transfer member comprises an annular plate 114; the ball end 113 of the spring plunger abuts against the first support member 102, and the adjustment end 105 of the spring plunger is disposed on the annular plate 114; the tail 111 of the engine is fixed to the first ring 115 and the engine is coaxial with the ring plate 114.
It is worth noting that: the number of the spring plungers 112 is the same as that of the axial force sensors 103, and the spring plungers 112 and the axial force sensors 103 are alternately arranged on the circumference of the first transmission member at equal intervals; in the actual use process, the pre-tightening effect can be realized by adjusting the adjusting end 105 of the spring plunger, namely, the compression amount of the spring plunger 112, so that each axial force sensor 103 is ensured to work in an accurate measuring range, and the influence of zero drift of the axial force sensor 103 is eliminated.
Furthermore, the effect of adjusting the pretightening force of the single axial force sensor 103 is realized by uniformly distributing the spring plungers 112 in the circumferential direction, the pretightening force adjusting effect is good, the precision is high, and the pretightening force does not influence the numerical value of the axial force sensor 103.
In this embodiment, the third support member shown in connection with fig. 1, 4 and 5 comprises a first circular ring 115; the second transmission member 108 includes a support rod 116, a pulley 117 disposed at one end of the support rod 116, and a first nut 118 for fixing the support rod 116 to the first ring 115; the pulley 117 is in contact with the head 110 of the motor.
In the embodiment, the second transmission member 108 is used for transmitting the thrust of the engine to the first circular ring 115, and in the embodiment, the second transmission member 108 transmits the thrust of the engine by means of the pulley 117, so that a purely rigid connection between the first circular ring 115 and the head 110 of the engine is avoided, axial friction is reduced to the greatest extent under the condition of accurately capturing the radial displacement of the engine, and the axial thrust measurement module 100 is ensured not to be interfered during the operation of the engine.
The first nuts 118 are provided with two, that is, the pulley 117 and the support rod 116 are fixed by a double nut to realize radial clamping, so as to ensure the transmission of radial thrust. In addition, a bidirectional adjusting space is reserved while the engine is clamped, the freedom degree is provided for adjusting the pretightening force, and the rocket engine with different outer diameters can be compatible.
In this embodiment, the rocket engine thrust vector measuring device further includes a support table 119; the first support member 102 includes a first support riser 120 and a support gusset 121; the first supporting riser 120 is perpendicular to one end of the supporting table 119, one end of the supporting angle plate 121 is fixed to the supporting table 119, the other end of the supporting angle plate is fixed to the first supporting riser 120, and the supporting angle plate 121 is used for providing axial support for the first supporting riser 120.
Specifically, the second support member 106 includes a second support riser 122 and a second annular ring 123 disposed on the second support riser 122; the second support riser 122 is perpendicular to the other end of the support table 119.
Specifically, a counter bore 124 is formed in the second ring 123, one end of the radial force sensor 107 is fixed to the first ring 115, and the other end of the radial force sensor passes through the counter bore 124 and is fixed to the second ring 123 through a second nut 125, in this embodiment, the counter bore 124 is adopted, so that field assembly is facilitated, and mutual interference between the radial force sensors 107 is avoided; the second nuts 125 are provided in two, and the two nuts are also fixed, so that tension or pressure pre-tightening can be respectively realized.
In summary, the thrust vector measuring device of the rocket engine should ensure that the circular ring plate 114 is well connected with the tail part 111 of the engine when being assembled. Adjusting the spring plunger 112 to be in a squeezed state, and enabling the spring plunger 112 to be screwed into the middle section of the axial force sensor 103 to a length slightly longer than that of the middle section of the axial force sensor 103 as shown in fig. 7, so that the pretightening force is always ensured to exist in the assembling process, and the axial force sensor 103 is prevented from exceeding the measuring range due to the assembling error; then, the second supporting member 106 is installed, and the radial force sensor 107 is connected with the second ring 123; finally, the second ring 123 is slid in from the head 110 of the engine, so that the three radial force sensors 107 are assembled without any external force.
It is worth mentioning that: the number of the axial force sensors 103 is preferably four, and the four axial force sensors 103 are arranged at equal intervals along the circumferential direction of the annular plate 114; the radial force sensors 107 are preferably three, and the three radial force sensors 107 are arranged at equal intervals along the circumferential direction of the second ring 123. Normally, the four axial force sensors 103 are always in tension, and further, the four axial force sensors 103 can be always in tension by adjusting the four spring plungers 112 to apply pre-tension. For the three radial force sensors 107, when the three radial force sensors 107 are pre-tensioned, the three radial force sensors are tensioned or compressed, and generally the three radial force sensors are compressed, the first ring 115 can be further clamped on the head 110 of the engine when the three radial force sensors 107 are pre-tensioned and compressed, so that the first ring 115 is ensured to be rigidly connected with the head 110 of the engine.
Example two
Referring to fig. 8, the present application further provides a method for measuring thrust vectors of a rocket engine, including the following steps:
step 100: establishing a three-dimensional coordinate system and defining parameters;
step 200: calculating the thrust of the engine from the readings of the axial force sensor 103 and the readings of the radial force sensor 107;
step 300: calculating the moment of the thrust F of the engine in the coordinate axis direction according to the three-dimensional coordinate system;
step 400: and establishing an equation set by utilizing moment balance, and calculating the thrust eccentricity and the thrust eccentricity angle.
Specifically, step 100 specifically includes: establishing a three-dimensional coordinate system by taking the center of the first transmission component as an origin; defining the radial force sensor 107 to be positively acted upon by a compressive force, respectively denoted as F r1 、F r2 、F r3 A center distance of any of the radial force sensors 107 to the third support member is r; defining the axial force sensor 103 as being positively tensioned, denoted F z1 、F z2 、F z3 、F z4 A center distance d from any of the axial force sensors 103 to the first transmission member; defining an axial distance LG between a center of mass of the engine and a center of a three-dimensional coordinate system, and defining an axial distance L between a center of the third support member and a center of a three-dimensional coordinate system r (ii) a Defining the thrust of the engine as F, and the thrust eccentricity P components of the engine are respectively P x 、P y The gravity of the engine is G;
specifically, step 200 specifically includes: by utilizing the force balance principle, three components F of the thrust F of the engine under a three-dimensional coordinate system x 、F y 、F z The indication with the axial force sensor 103 and the indication with the radial force sensor 107 satisfies equation (1):
Figure BDA0003581943160000131
the thrust force F of the engine can be obtained according to the formula (1) and is shown as the formula (2):
Figure BDA0003581943160000132
specifically, step 300 specifically includes: moments of the axial force sensor 103 and the radial force sensor 107 in the x-axis direction in the three-dimensional coordinate system
Figure BDA0003581943160000133
Moments of the axial force sensor 103 and the radial force sensor 107 in the y-axis direction in the three-dimensional coordinate system
Figure BDA0003581943160000134
As shown in equation (3):
Figure BDA0003581943160000135
moment of thrust F of the engine in the x-axis direction in the three-dimensional coordinate system
Figure BDA0003581943160000136
Moment of thrust F of the engine in the y-axis direction in the three-dimensional coordinate system
Figure BDA0003581943160000137
As shown in equation (4):
Figure BDA0003581943160000138
specifically, step 400 specifically includes: the torque according to the engine thrust F is balanced with the torque of the axial force sensor 103 and the torque of the radial force sensor 107, and the formula (5):
Figure BDA0003581943160000139
calculating a component P of a thrust eccentricity P of the engine from equations (3) to (5) x 、P y (ii) a Calculating a thrust eccentricity P of the engine and a thrust eccentricity argument phi of the engine by using a formula (6);
Figure BDA0003581943160000141
to sum up, rocket engine thrust vector measuring device comprises axial thrust measurement module 100 and radial thrust measurement module 101, based on the design of two modularization, in the occasion that does not require to measure engine thrust eccentricity and eccentric argument, engine thrust measurement work can be accomplished to the axial thrust measurement module 100 of exclusive use, and is worth noting: when the axial thrust measuring module 100 is used alone, the installation and pretension adjustment steps are completely the same as those when the double modules are used, and in the calculation, the thrust calculation formula (1) F is used x 、F y Axial thrust can be calculated if the axial thrust is 0.
Finally, it should be noted that: the above embodiments are only used for illustrating the technical solutions of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present application.

Claims (10)

1. A rocket engine thrust vector measuring device is characterized by comprising an axial thrust measuring module and a radial thrust measuring module;
the axial thrust measurement module includes a first support member, an axial force sensor, an adjustment member, and a first transmission member; the axial force sensor and the adjustment member are disposed between the first support member and the first transmission member for fixing a tail of an engine; the number of the axial force sensors is at least three, and the axial force sensors extend along the axial direction of the engine;
the radial thrust measurement module includes a second support member, a radial force sensor, a second transmission member, and a third support member; one end of the second transmission member is disposed on a third support member and the other end contacts a head of the engine, and one end of the radial force sensor is fixed to the third support member and the other end is disposed on the second support member; the number of the radial force sensors is at least three and extends in a radial direction of the engine.
2. A rocket engine thrust vector measuring device according to claim 1, wherein said adjusting member comprises a spring plunger;
the ball end of the spring plunger abuts against the first support member, and the adjusting end of the spring plunger is arranged on the first transmission member;
the tensile force applied to the axial force sensor can be adjusted by adjusting the adjusting end of the spring plunger.
3. A rocket engine thrust vector measuring device according to claim 2, wherein the number of said spring plungers is the same as the number of said axial force sensors, and said spring plungers and said axial force sensors are alternately arranged at equal intervals on the rim of said first transmission member.
4. A rocket engine thrust vector measuring device according to claim 1, wherein said first transfer member comprises a circular ring plate;
the tail of the engine is fixed on the circular ring plate, and the engine is coaxial with the first circular ring plate.
5. A rocket engine thrust vector measuring device according to claim 1, wherein said third support member comprises a first annular ring;
the second transmission component comprises a support rod, a pulley arranged at one end of the support rod and a first nut used for fixing the support rod on the first circular ring; the pulley is in contact with a head of the engine.
6. A rocket engine thrust vector measuring device according to claim 5, further comprising a support table;
the first support component comprises a first support vertical plate and a support angle plate; the first supporting vertical plate is perpendicular to one end of the supporting platform, one end of the supporting angle plate is fixed on the supporting platform, and the other end of the supporting angle plate is fixed on the first supporting vertical plate;
the second support component comprises a second support vertical plate and a second circular ring arranged on the second support vertical plate; the second supporting vertical plate is perpendicular to the other end of the supporting platform.
7. A rocket engine thrust vector measuring device according to claim 6, wherein said second ring is provided with a counter bore, one end of said radial force sensor is fixed to said first ring, and the other end of said radial force sensor passes through said counter bore and is fixed to said second ring by a second nut.
8. A rocket engine thrust vector measuring device according to claim 5, wherein the number of said axial force sensors is four, and the number of said radial force sensors is three.
9. A thrust vector measuring method based on the rocket engine thrust vector measuring device recited in claim 8, characterized by comprising the steps of:
establishing a three-dimensional coordinate system and defining parameters;
calculating thrust of the engine from the readings of the axial force sensors and the readings of the radial force sensors;
calculating the moment of the thrust F of the engine in the coordinate axis direction according to the three-dimensional coordinate system;
and establishing an equation set by utilizing moment balance, and calculating the thrust eccentricity and the thrust eccentricity angle.
10. The thrust vector measurement method according to claim 9,
establishing a three-dimensional coordinate system by taking the center of the first transmission component as an origin; defining the radial force sensor to be positive under the action of pressure, and respectively recording as F r1 、F r2 、F r3 A center distance of any of the radial force sensors to the third support member is r; defining the tensile force action of the axial force sensor as positive, respectively denoted as F z1 、F z2 、F z3 、F z4 A center distance d from any of the axial force sensors to the first transfer member; defining an axial distance LG between a center of mass of the engine and a center of a three-dimensional coordinate system, and defining an axial distance L between a center of the third support member and a center of a three-dimensional coordinate system r (ii) a Defining the thrust of the engine as F, and the thrust eccentricity P components of the engine are respectively P x 、P y The gravity of the engine is G;
by utilizing the force balance principle, three components F of the thrust F of the engine under a three-dimensional coordinate system x 、F y 、F z With the readings of the axial force sensor and the readings of the radial force sensor satisfying equation (1):
Figure FDA0003581943150000031
the thrust force F of the engine can be obtained according to the formula (1) and is shown as the formula (2):
Figure FDA0003581943150000032
the axial force sensor and the radial force sensor have moment in the x-axis direction in the three-dimensional coordinate system
Figure FDA0003581943150000033
Moments of the axial force sensor and the radial force sensor in the y-axis direction in the three-dimensional coordinate system
Figure FDA0003581943150000034
As shown in equation (3):
Figure FDA0003581943150000041
moment of thrust F of the engine in the x-axis direction in the three-dimensional coordinate system
Figure FDA0003581943150000042
Moment of thrust F of the engine in the y-axis direction in the three-dimensional coordinate system
Figure FDA0003581943150000043
As shown in equation (4):
Figure FDA0003581943150000044
the torque according to the thrust F of the engine is balanced with the torque of the axial force sensor and the torque of the radial force sensor, and the formula (5):
Figure FDA0003581943150000045
determining the engine according to equations (3) to (5)Component P of thrust eccentricity P of machine x 、P y (ii) a Calculating a thrust eccentricity P of the engine and a thrust eccentricity argument phi of the engine by using a formula (6);
Figure FDA0003581943150000046
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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6032545A (en) * 1998-04-17 2000-03-07 California Polytechnic State University Foundation Nozzle flow thrust vector measurement
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
CN109115510A (en) * 2018-10-01 2019-01-01 北京航天三发高科技有限公司 A kind of Time series analysis and its accidentally method for determining difference
CN111735565A (en) * 2020-04-13 2020-10-02 北京航空航天大学 Method and device for measuring thrust parameters of thrust engine
WO2021128761A1 (en) * 2019-12-23 2021-07-01 马洪文 Distributed multi-dimensional force measurement system and measurement method

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6032545A (en) * 1998-04-17 2000-03-07 California Polytechnic State University Foundation Nozzle flow thrust vector measurement
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
CN109115510A (en) * 2018-10-01 2019-01-01 北京航天三发高科技有限公司 A kind of Time series analysis and its accidentally method for determining difference
WO2021128761A1 (en) * 2019-12-23 2021-07-01 马洪文 Distributed multi-dimensional force measurement system and measurement method
CN111735565A (en) * 2020-04-13 2020-10-02 北京航空航天大学 Method and device for measuring thrust parameters of thrust engine

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