CN114858334B - Rocket engine thrust vector measurement device and thrust vector measurement method - Google Patents

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

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Publication number
CN114858334B
CN114858334B CN202210354761.1A CN202210354761A CN114858334B CN 114858334 B CN114858334 B CN 114858334B CN 202210354761 A CN202210354761 A CN 202210354761A CN 114858334 B CN114858334 B CN 114858334B
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thrust
engine
force sensor
axial
radial
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CN114858334A (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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    • 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 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 supporting member, an axial force sensor, an adjusting member and a first transmission member; the axial force sensor is at least three; the radial thrust measurement module comprises a second support member, a radial force sensor, a second transmission member and a third support member; the radial force sensor is at least three. The engine thrust 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 moment of the thrust of the engine in the coordinate axis direction of the three-dimensional coordinate system; the eccentricity and the eccentric radial angle of the thrust of the engine can be solved by utilizing the moment balance to establish an equation set.

Description

Rocket engine thrust vector measurement device and thrust vector measurement method
Technical Field
The application relates to the technical field of aerospace, in particular to a rocket engine thrust vector measuring device and a 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, only a thrust value is commonly measured, a thrust vector (such as a thrust eccentricity) is difficult to measure, and the thrust measurement requirement of the existing rocket engine cannot be met.
Therefore, there is a need for a rocket engine thrust vector measurement device, which solves the technical problems in the prior art to a certain extent.
Disclosure of Invention
The utility model aims to provide a rocket engine thrust vector measuring device and thrust vector measuring method to solve to a certain extent and adopt ordinary pressure sensor to carry out thrust measurement in prior art, can only measure thrust numerical value, the technical problem of the vector of difficult measurement thrust.
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 supporting member, an axial force sensor, an adjusting member and a first transmission member; the axial force sensor and the adjusting member are arranged between the first supporting member and the first transmission member, and the first transmission member is used for fixing the tail part of the 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 comprises 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 arranged on a third supporting member, the other end of the second transmission member contacts the head of the engine, one end of the radial force sensor is fixed on the third supporting member, and the other end of the radial force sensor is arranged on the second supporting member; the number of the radial force sensors is at least three and extends in the 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 is abutted against the first supporting member, and the adjusting end of the spring plunger is arranged on the first transmission member;
and the adjusting end of the spring plunger is adjusted to adjust the tensile force applied by the axial force sensor.
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 the edge of the first transmission member at equal intervals.
In the above technical solution, further, the first transmission member includes a circular plate; the tail of the engine is fixed on the annular plate, and the engine is coaxial with the first annular plate.
In the above technical solution, further, the third supporting member includes a first ring; the second transmission member comprises a supporting rod, a pulley arranged at one end of the supporting rod and a first nut used for fixing the supporting rod on the first circular ring; the pulley is in contact with the head of the engine.
In the technical scheme, the device further comprises a supporting table; the first support member includes a first support riser and a support gusset; the first supporting vertical plate is perpendicular to one end of the supporting table, one end of the supporting angle plate is fixed to the supporting table, and the other end of the supporting angle plate is fixed to the first supporting vertical plate;
the second supporting member comprises a second supporting vertical plate and a second circular ring arranged on the second supporting vertical plate; the second supporting vertical plate is perpendicular to the other end of the supporting table.
In the above technical scheme, 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 measurement method, which comprises the following steps of establishing a three-dimensional coordinate system and defining parameters;
calculating the thrust of the engine according to the indication of the axial force sensor and the indication of the radial force sensor;
according to the three-dimensional coordinate system, calculating moment of thrust F of the engine in the coordinate axis direction;
and (5) establishing an equation set by utilizing moment balance, and calculating the thrust eccentricity and the thrust eccentric 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 that the radial force sensor is positively stressed and respectively marked as F r1 、F r2 、F r3 Any of the radial force sensors to the third support memberThe center distance of (2) is r; defining that the tensile force of the axial force sensor is positive and respectively marked 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 the axial distance LG between the center of mass of the engine and the center of the three-dimensional coordinate system, and defining the axial distance L between the center of the third support member and the center of the three-dimensional coordinate system r The method comprises the steps of carrying out a first treatment on the surface of the Defining 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, the thrust force F of the engine has three components F under a three-dimensional coordinate system x 、F y 、F z The indication with the axial force sensor and the indication with the radial force sensor satisfy the formula (1):
Figure BDA0003581943160000041
the thrust F of the engine can be found from formula (1) as in formula (2):
Figure BDA0003581943160000042
moment of the axial force sensor and the radial force sensor in the x-axis direction in the three-dimensional coordinate system
Figure BDA0003581943160000043
Moment of the axial force sensor, the radial force sensor in the y-axis direction in the three-dimensional coordinate system>
Figure BDA0003581943160000049
As shown in formula (3):
Figure BDA0003581943160000044
moment of thrust F of engine in x-axis direction in the three-dimensional coordinate system
Figure BDA0003581943160000045
Moment of thrust F of the engine in the y-axis direction in said three-dimensional coordinate system +.>
Figure BDA0003581943160000046
As shown in formula (4):
Figure BDA0003581943160000047
according to the moment balance of the thrust force F of the engine and the moment balance of the axial force sensor and the radial force sensor, the formula (5) is:
Figure BDA0003581943160000048
obtaining a component P of the thrust eccentricity P of the engine according to formulas (3) - (5) x 、P y The method comprises the steps of carrying out a first treatment on the surface of the Calculating the thrust eccentricity P of the engine and the thrust eccentric amplitude phi of the engine by using a formula (6);
Figure BDA0003581943160000051
compared with the prior art, the beneficial effects of this application are:
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 supporting member, an axial force sensor, an adjusting member and a first transmission member; the axial force sensor and the adjusting member are arranged between the first supporting member and the first transmission member, and the first transmission member is used for fixing the tail part of the 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 comprises 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 arranged on a third supporting member, the other end of the second transmission member contacts the head of the engine, one end of the radial force sensor is fixed on the third supporting member, and the other end of the radial force sensor is arranged on the second supporting member; the number of the radial force sensors is at least three and extends in the radial direction of the engine.
In summary, the present application can calculate engine thrust according to the data of the axial force sensor and the radial force sensor; the axial force sensor module center is taken 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; the eccentricity and the eccentric radial angle of the thrust of the engine can be solved by utilizing the moment balance to establish an equation set; further, by adopting the structure, the thrust of the engine, the eccentricity of the thrust of the engine and the eccentric radial angle can be measured by using the common tension 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 the thrust of the engine according to the indication of the axial force sensor and the indication of the radial force sensor;
according to the three-dimensional coordinate system, calculating moment of thrust F of the engine in the coordinate axis direction;
and (5) establishing an equation set by utilizing moment balance, and calculating the thrust eccentricity and the thrust eccentric angle.
Specifically, the rocket engine thrust vector measurement method has both thrust value measurement and thrust eccentricity measurement. Meanwhile, the thrust numerical 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 embodiments of the present application or the technical solutions in the prior art, the drawings that are needed 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 application, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic diagram of the overall structure of a rocket engine thrust vector measurement 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 device according to an embodiment of the present disclosure;
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 device according to an embodiment of the present disclosure;
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 view of a first transmission member and an adjustment member in a rocket engine thrust vector measurement device according to an embodiment of the present disclosure;
FIG. 7 is an enlarged view 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 disclosure.
Reference numerals:
100-an axial thrust measurement module; 101-a radial thrust measurement module; 102-a first support member; 103-axial force sensor; 105—an adjustment end of a spring plunger; 106-a second support member; 107-radial force sensor; 108-a second transfer member; 110-the head of the engine; 111-tail of the engine; 112-spring plunger; 113-ball end of spring plunger; 114-a circular plate; 115-a first ring; 116-supporting rods; 117-pulleys; 118-a first nut; 119-supporting table; 120-a first support riser; 121-supporting the corner plate; 122-a second support riser; 123-a second ring; 124-counter bore; 125-second nut.
Detailed Description
The following description of the embodiments of the present application will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown.
The components of the embodiments of the present application, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the present application, as provided in the accompanying drawings, is not intended to limit the scope of the application, as claimed, but is merely representative of selected embodiments of the application.
All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure.
In the description of the present application, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of description of the present application and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific 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 explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art in a specific context.
Example 1
Rocket engine thrust vector measuring devices according to some embodiments of the present application are described below with reference to fig. 1 to 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 transmitting member, and the axial force sensor 103 can be ensured to work in an accurate measuring range by adjusting the adjusting member, 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 111 of the engine, and the tail 111 of the engine is preferably fixed to the first transmission member by eight M8 bolts, and thrust of the engine is transmitted by the first transmission member and can be finally detected by the axial force sensor 103.
The radial thrust measurement module 101 comprises a second support member 106, a radial force sensor 107, a second transfer member 108 and a third support member; one end of the second transmission member 108 is disposed on a third support member and the other end contacts a head 110 of the engine, and one end of the radial force sensor 107 is fixed to the third support member and the other end is disposed on the second support member 106;
notably, are: 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; the stability of the axial force sensor 103 and the radial force sensor 107 for detecting the thrust of the engine is ensured; 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. a parameter of the thrust of the engine in the axial direction can be detected by the axial force sensor 103, and a parameter of the thrust of the engine in the radial direction can be detected by the radial force sensor 107.
In summary, the present application can calculate the engine thrust from the data of the axial force sensor 103 and the radial force sensor 107; then taking the center of the axial force sensor 103 module as a coordinate origin and establishing a three-dimensional coordinate system, so that the moment of the thrust of the engine in the coordinate axis direction of the three-dimensional coordinate system can be calculated; the eccentricity and the eccentric radial angle of the thrust of the engine can be solved by utilizing the moment balance to establish an equation set; further, by adopting the structure, the thrust of the engine, the eccentricity of the thrust of the engine and the eccentric radial angle can be measured by using the common tension pressure sensor.
In this embodiment, as shown in connection with fig. 1, 2 and 3, the adjustment member comprises a spring plunger 112 and the first transfer member comprises a circular plate 114; the ball end 113 of the spring plunger is abutted against the first supporting member 102, and the adjusting end 105 of the spring plunger is arranged 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.
Notably, are: 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 and equally spaced on the circumference of the first transmission member; in the actual use process, the pretension 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 the accurate measuring range, and the influence of zero drift of the axial force sensor 103 is eliminated.
Further, by means of circumferentially uniformly distributing the spring plungers 112, the effect of adjusting the pretightening force of the single axial force sensor 103 is achieved, the pretightening force adjusting effect is good, the pretightening precision is high, and the pretightening force does not affect the numerical value of the axial force sensor 103.
In this embodiment, the third support member described in connection with fig. 1, 4 and 5 comprises a first 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 engine.
The second transmission member 108 is configured to transmit the thrust of the engine to the first ring 115, in this embodiment, the second transmission member 108 transmits the thrust of the engine by adopting a pulley 117, so as to avoid a pure rigid connection between the first ring 115 and the head 110 of the engine, and minimize the axial friction under the condition of precisely capturing the radial displacement of the engine, thereby ensuring that the axial thrust measurement module 100 is not disturbed during the working process of the engine.
The first nut 118 is provided with two nuts, that is, the pulley 117 and the supporting rod 116 are fixed by double nuts to realize radial clamping, so as to ensure the transmission of radial pushing force. In addition, the two-way adjusting space is reserved while the engine is clamped, the freedom degree is provided for pretightening force adjustment, 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 on the supporting table 119, the other end of the supporting angle plate 121 is fixed on 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 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, the second ring 123 is provided with a counterbore 124, one end of the radial force sensor 107 is fixed on the first ring 115, and the other end passes through the counterbore 124 and is fixed on the second ring 123 through a second nut 125, in this embodiment, the counterbore 124 is adopted, so that the on-site assembly is convenient, and the mutual interference between the radial force sensors 107 is avoided; the second nuts 125 are provided with two, and the same double-nut fixing mode is adopted, so that tension or pressure pre-tightening can be respectively realized.
In summary, the rocket engine thrust vector measuring device should ensure that the ring plate 114 is well connected with the tail 111 of the engine during assembly. The spring plunger 112 is adjusted to be in a pressed state, and as shown in fig. 7, the spring plunger 112 is screwed into the middle section of the axial force sensor 103 to be slightly longer, so that pretightening force is always generated in the assembly process, and the axial force sensor 103 is prevented from exceeding the measuring range due to assembly errors; then the second supporting member 106 is installed, and the radial force sensor 107 is connected with the second circular ring 123 first; finally, the second ring 123 is slid in from the head 110 of the engine, so that the assembly of the three radial force sensors 107 is completed without any external force.
Noteworthy are: 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 annular ring 123. Typically, 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 a pre-tightening force. For the three radial force sensors 107, the tension or compression requirements are met during pre-tightening, and the compression is generally carried out during pre-tightening of the radial force sensors 107, so that the first annular ring 115 can be further clamped on the head 110 of the engine, and the first annular 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 rocket engine thrust vector measurement method, which includes the following steps:
step 100: establishing a three-dimensional coordinate system and defining parameters;
step 200: calculating the thrust of the engine according to the indication of the axial force sensor 103 and the indication of the radial force sensor 107;
step 300: according to the three-dimensional coordinate system, calculating moment of thrust F of the engine in the coordinate axis direction;
step 400: and (5) establishing an equation set by utilizing moment balance, and calculating the thrust eccentricity and the thrust eccentric angle.
Specifically, step 100 specifically includes: with the first transmission mechanismThe center of the piece is used as an origin to establish a three-dimensional coordinate system; define that the radial force sensor 107 is positively stressed and is respectively denoted as F r1 、F r2 、F r3 A center distance r of any of the radial force sensors 107 to the third support member; the axial force sensor 103 is defined to be positive under tensile force and is respectively marked as 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 the axial distance LG between the center of mass of the engine and the center of the three-dimensional coordinate system, and defining the axial distance L between the center of the third support member and the center of the three-dimensional coordinate system r The method comprises the steps of carrying out a first treatment on the surface of the Defining 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, the thrust force F of the engine has three components F 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 satisfy the formula (1):
Figure BDA0003581943160000131
the thrust F of the engine can be found from formula (1) as in formula (2):
Figure BDA0003581943160000132
specifically, step 300 specifically includes: moment of the axial force sensor 103, the radial force sensor 107 in the x-axis direction in the three-dimensional coordinate system
Figure BDA0003581943160000133
Moment +_of the axial force sensor 103, the radial force sensor 107 in the y-axis direction in the three-dimensional coordinate system>
Figure BDA0003581943160000134
As shown in formula (3):
Figure BDA0003581943160000135
moment of thrust F of engine in x-axis direction in the three-dimensional coordinate system
Figure BDA0003581943160000136
Moment of thrust F of the engine in the y-axis direction in said three-dimensional coordinate system +.>
Figure BDA0003581943160000137
As shown in formula (4):
Figure BDA0003581943160000138
specifically, step 400 specifically includes: according to the torque balance between the thrust force F of the engine and the torque of the axial force sensor 103 and the radial force sensor 107, the following formula (5) is given:
Figure BDA0003581943160000139
obtaining a component P of the thrust eccentricity P of the engine according to formulas (3) - (5) x 、P y The method comprises the steps of carrying out a first treatment on the surface of the Calculating the thrust eccentricity P of the engine and the thrust eccentric amplitude phi of the engine by using a formula (6);
Figure BDA0003581943160000141
in summary, the rocket engine thrust vector measuring device consists of an axial thrust measuring module 100 and a radial thrust measuring module 101, and based on the design of double modules, the axial thrust measuring module is independently used in the occasion of not requiring to measure the thrust eccentricity and the eccentric amplitude of the engine100, it is noted that: when the axial thrust measuring module 100 is used alone, the installation and pre-tightening adjustment steps are exactly the same as when the dual modules are used, and F in the thrust calculation formula (1) is caused to be calculated x 、F y The axial thrust can be calculated by 0.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution 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 scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the corresponding technical solutions from the scope of the technical solutions of the embodiments of the present application.

Claims (9)

1. The 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 comprises a first supporting member, an axial force sensor, an adjusting member and a first transmission member; the axial force sensor and the adjusting member are arranged between the first supporting member and the first transmission member, and the first transmission member is used for fixing the tail part of the 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 comprises 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 arranged on a third supporting member, the other end of the second transmission member contacts the head of the engine, one end of the radial force sensor is fixed on the third supporting member, and the other end of the radial force sensor is arranged on the second supporting member; the number of the radial force sensors is at least three and extends along the radial direction of the engine;
the third support member includes a first annular ring;
the second transmission member comprises a supporting rod, a pulley arranged at one end of the supporting rod and a first nut used for fixing the supporting rod on the first circular ring; the pulley is in contact with the head of the engine.
2. A rocket engine thrust vector measurement device according to claim 1, wherein the adjustment member comprises a spring plunger;
the ball end of the spring plunger is abutted against the first supporting member, and the adjusting end of the spring plunger is arranged on the first transmission member;
and the adjusting end of the spring plunger is adjusted to adjust the tensile force applied by the axial force sensor.
3. A rocket engine thrust vector measurement device according to claim 2, wherein the number of spring plungers is the same as the number of axial force sensors, and the spring plungers and the axial force sensors are alternately arranged at the edge of the first transmission member at equal intervals.
4. A rocket engine thrust vector measurement device according to claim 1, wherein the first transfer member comprises a circular plate;
the tail of the engine is fixed on the annular plate, and the engine is coaxial with the first annular plate.
5. A rocket engine thrust vector measurement device according to claim 1, further comprising a support table;
the first support member includes a first support riser and a support gusset; the first supporting vertical plate is perpendicular to one end of the supporting table, one end of the supporting angle plate is fixed to the supporting table, and the other end of the supporting angle plate is fixed to the first supporting vertical plate;
the second supporting member comprises a second supporting vertical plate and a second circular ring arranged on the second supporting vertical plate; the second supporting vertical plate is perpendicular to the other end of the supporting table.
6. A rocket engine thrust vector measurement device according to claim 5 wherein a counterbore is formed in the second annular ring, one end of the radial force sensor is fixed to the first annular ring, and the other end passes through the counterbore and is fixed to the second annular ring by a second nut.
7. A rocket engine thrust vector measurement device according to claim 1, wherein the number of axial force sensors is four and the number of radial force sensors is three.
8. A thrust vector measurement method based on the rocket engine thrust vector measurement device of claim 7, comprising the steps of:
establishing a three-dimensional coordinate system and defining parameters;
calculating the thrust of the engine according to the indication of the axial force sensor and the indication of the radial force sensor;
calculating thrust of engine according to three-dimensional coordinate system
Figure QLYQS_1
Moment in the coordinate axis direction;
and (5) establishing an equation set by utilizing moment balance, and calculating the thrust eccentricity and the thrust eccentric angle.
9. The method for measuring a thrust vector according to claim 8, wherein,
establishing a three-dimensional coordinate system by taking the center of the first transmission member as an origin; defining that the radial force sensor is positively stressed and respectively recorded as
Figure QLYQS_14
、/>
Figure QLYQS_4
、/>
Figure QLYQS_11
The center distance of any of the radial force sensors to the third support member is +.>
Figure QLYQS_9
The method comprises the steps of carrying out a first treatment on the surface of the The tensile force of the axial force sensor is defined as positive, and the force is respectively marked as +.>
Figure QLYQS_15
、/>
Figure QLYQS_16
、/>
Figure QLYQS_17
、/>
Figure QLYQS_7
The center distance of any of the axial force sensors to the first transmission member is +.>
Figure QLYQS_13
The method comprises the steps of carrying out a first treatment on the surface of the Defining the axial distance of the centre of mass of the engine from the centre of the three-dimensional coordinate system as +.>
Figure QLYQS_2
Defining the axial distance between the center of the third support member and the center of the three-dimensional coordinate system as +.>
Figure QLYQS_10
The method comprises the steps of carrying out a first treatment on the surface of the Defining the thrust of the engine as +.>
Figure QLYQS_5
The thrust eccentricity of the engine +.>
Figure QLYQS_12
The components are +.>
Figure QLYQS_6
、/>
Figure QLYQS_8
The gravity of the engine is +.>
Figure QLYQS_3
；
By utilizing the force balance principle, the thrust F of the engine has three components in a three-dimensional coordinate systemF x 、F y 、F z The indication with the axial force sensor and the indication with the radial force sensor satisfy the formula (1):
Figure QLYQS_18
（1）
the thrust F of the engine can be found from formula (1) as in formula (2):
Figure QLYQS_19
（2）
the axial force sensor and the radial force sensor are arranged in the three-dimensional coordinate system
Figure QLYQS_20
Moment in the axial direction->
Figure QLYQS_21
The axial force sensor and the radial force sensor are +_in the three-dimensional coordinate system>
Figure QLYQS_22
Moment in the axial direction->
Figure QLYQS_23
As shown in formula (3):
Figure QLYQS_24
（3）
thrust of engine
Figure QLYQS_25
In the three-dimensional coordinate system +.>
Figure QLYQS_26
Moment in the axial direction->
Figure QLYQS_27
Thrust of engine->
Figure QLYQS_28
In the three-dimensional coordinate system +.>
Figure QLYQS_29
Moment in the axial direction->
Figure QLYQS_30
As shown in formula (4):
Figure QLYQS_31
（4）
based on thrust of engine
Figure QLYQS_32
The moment balance of the axial force sensor and the radial force sensor is as follows:
Figure QLYQS_33
（5）
obtaining the thrust eccentricity of the engine according to formulas (3) - (5)
Figure QLYQS_34
Component (S)>
Figure QLYQS_35
、/>
Figure QLYQS_36
The method comprises the steps of carrying out a first treatment on the surface of the Calculating the thrust eccentricity +.>
Figure QLYQS_37
And the thrust eccentric amplitude angle of the engine +.>
Figure QLYQS_38
；
Figure QLYQS_39
（6）。
CN202210354761.1A 2022-04-06 2022-04-06 Rocket engine thrust vector measurement device and thrust vector measurement method Active CN114858334B (en)

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CN109084982B (en) * 2018-08-29 2020-04-03 西安航天动力试验技术研究所 High-thrust rocket engine three-dimensional force measuring device and measuring method
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