CN112906129A - Rocket modal parameter measuring method and system - Google Patents
Rocket modal parameter measuring method and system Download PDFInfo
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- CN112906129A CN112906129A CN202110126141.8A CN202110126141A CN112906129A CN 112906129 A CN112906129 A CN 112906129A CN 202110126141 A CN202110126141 A CN 202110126141A CN 112906129 A CN112906129 A CN 112906129A
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- 238000005259 measurement Methods 0.000 claims abstract description 27
- 238000012545 processing Methods 0.000 claims description 14
- 230000001133 acceleration Effects 0.000 claims description 12
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P15/00—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P15/00—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration
- G01P15/02—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses
- G01P15/08—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses with conversion into electric or magnetic values
- G01P15/09—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses with conversion into electric or magnetic values by piezoelectric pick-up
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P15/00—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration
- G01P15/02—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses
- G01P15/08—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses with conversion into electric or magnetic values
- G01P15/12—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses with conversion into electric or magnetic values by alteration of electrical resistance
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
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Abstract
The invention discloses a method and a system for measuring rocket modal parameters, which relate to the technical field of rocket testing and comprise the following steps: step S1, selecting any cabin connecting surface of the rocket, and calculating N bending moments borne by the cabin connecting surface according to the load borne by N characteristic moments in the rocket flying process; step S2, determining N groups of rocket mode test horizontal suspension parameters corresponding to the cabin section connecting surface according to N bending moments borne by the cabin section connecting surface, wherein the rocket mode test horizontal suspension parameters comprise the number of hoisting points, the positions of the hoisting points and the tension of the hoisting points; step S3, horizontally suspending the rocket for N times according to the N groups of rocket modal test horizontal suspension parameters of the cabin section connecting surface, and measuring the rocket modal parameters of the cabin section connecting surface in the N times horizontal suspension state. When the modal parameters of the rocket are measured, the bending moment load borne by the butt joint surfaces of the selected cabin sections is close to the bending moment load of actual flight of the rocket, so that the measurement accuracy of the modal parameters of the rocket is high, and the measurement cost is low.
Description
Technical Field
The invention relates to the technical field of rocket mechanical testing, in particular to a method and a system for measuring modal parameters of a rocket.
Background
The modal parameter measurement is a measurement method for measuring the inherent vibration characteristic of a structure based on the resonance principle. Due to the particularity of the application of the carrier rocket, the safety requirement of the carrier rocket is very high, so that strict modal parameter measurement needs to be carried out before the carrier rocket is used.
For the measurement of modal parameters of a launch vehicle, a relatively extensive measurement method is currently adopted for the measurement of elastic suspension in a vertical state. In the vertical elastic suspension measurement method, the rocket is elastically suspended in the vertical state, so that the boundary condition is consistent with the free state, but the boundary condition is different from the actual flight state, and the measurement result has certain error. In addition, the rocket needs a large vertical space in a vertical state, and needs a tower for measurement, so that the measurement cost is high, the operation is difficult, and the part related to high-altitude operation has certain risk.
Therefore, it is necessary to design a method for measuring modal parameters of a rocket, so as to improve the accuracy of measuring the modal parameters of the carrier rocket and reduce the cost of measuring the modal parameters.
Disclosure of Invention
The embodiment of the invention provides a method and a system for measuring rocket modal parameters, which can solve the technical problems of low measurement precision and high measurement cost of the existing rocket modal parameters.
In a first aspect, a rocket modal parameter measuring method is provided, which includes the following steps:
selecting any cabin connecting surface of the rocket, and calculating N bending moments borne by the cabin connecting surface according to the load borne by the rocket at N characteristic moments in the flying process;
determining N groups of rocket mode test horizontal suspension parameters corresponding to the cabin section connecting surface according to the magnitude of N bending moments borne by the cabin section connecting surface, wherein the rocket mode test horizontal suspension parameters comprise the number of hoisting points, the positions of the hoisting points and the tension of the hoisting points;
and horizontally suspending the rocket for N times according to the N groups of rocket modal test horizontal suspension parameters of the cabin section connecting surface, and measuring the rocket modal parameters of the cabin section connecting surface in the N times of horizontal suspension state.
In some embodiments, said horizontally suspending the rocket for N times according to the N groups of rocket modal test horizontal suspension parameters of the cabin section connection surface, and measuring the rocket modal parameters of the cabin section connection surface in the N times horizontal suspension state, includes the following steps:
step S301, acquiring the number of hoisting points, the positions of the hoisting points and the hoisting point tension in the kth group of rocket mode test horizontal suspension parameters of the cabin section connecting surface;
step S302, selecting a corresponding number of horizontal suspension components according to the number of the suspension points;
step S303, moving the selected horizontal suspension component along the frame body according to the position of the lifting point, and connecting the selected horizontal suspension component with the rocket;
step S304, adjusting the tension of the selected horizontal suspension assembly according to the tension of the hoisting point;
step S305, measuring rocket modal parameters of the cabin section connecting surface in the kth horizontal suspension state;
in step S306, steps S301 to S305 are repeated so that k is 1,2, …, N, respectively.
In some embodiments, the measuring the rocket modal parameters of the cabin connecting surface in the k-th horizontal suspension state comprises the following steps:
arranging a plurality of test sensors on the rocket, and exciting the end part of the rocket by using an exciting piece;
and acquiring excitation data of the excitation piece and data acquired by the plurality of test sensors after the rocket is excited by using data processing equipment, and calculating and processing to obtain rocket modal parameters of the cabin connecting surface in the kth horizontal suspension state.
In some embodiments, the nacelle section connection surfaces include at least a rocket nacelle section breakaway connection surface and a floating connection surface.
In a second aspect, there is provided a rocket modal parameter measurement system, comprising:
the computing device is used for selecting any cabin connecting surface of the rocket and computing N bending moments borne by the cabin connecting surface according to the load borne by the N characteristic moments in the rocket flying process; the system is also used for determining N groups of rocket mode test horizontal suspension parameters corresponding to the cabin section connecting surface according to the N bending moments borne by the cabin section connecting surface, wherein the rocket mode test horizontal suspension parameters comprise the number of hoisting points, the positions of the hoisting points and the tension of the hoisting points;
the horizontal suspension device is used for horizontally suspending the rocket for N times according to the N groups of rocket modal test horizontal suspension parameters of the cabin section connecting surface;
and the measuring device is used for measuring the rocket modal parameters of the cabin section connecting surface in the N-time horizontal suspension state.
In some embodiments, the horizontal suspension device comprises:
a frame body;
the horizontal suspension components are horizontally arranged on the frame body at intervals, each horizontal suspension component is provided with a moving part and a suspension part, the moving parts are arranged on the frame body and can move along the frame body, the suspension parts are provided with a suspension rod and a suspension belt, the upper end of the suspension rod is connected with the moving parts, the lower end of the suspension rod is connected with one end of the suspension belt, and the other end of the suspension belt is used for being connected with a rocket.
In some embodiments, the strap is in two detachable sections, and a resilient suspension is provided between the two sections.
In some embodiments, a force sensor is disposed on the boom.
In some embodiments, the measurement device comprises:
a plurality of test sensors, which are used for being arranged on the rocket at intervals;
an exciter for exciting an end of the rocket;
and the data processing equipment is used for acquiring excitation data of the excitation piece and data acquired by the plurality of test sensors after the rocket is excited, and calculating and processing to obtain rocket modal parameters of the cabin section connecting surface.
In some embodiments, the test sensors include one or more of strain gauge acceleration sensors, piezoresistive acceleration sensors, and piezoelectric acceleration sensors.
The technical scheme provided by the invention has the beneficial effects that:
the embodiment of the invention provides a rocket modal parameter measuring method and a rocket modal parameter measuring system, wherein a connecting surface of any cabin section of a rocket is selected, N groups of rocket modal test horizontal suspension parameters are determined based on the load borne by N characteristic moments in the rocket flight process, the rocket is horizontally suspended for N times based on the N groups of rocket modal test horizontal suspension parameters, each time of horizontally suspending the rocket corresponds to the load borne by the connecting surface of the cabin section at the N characteristic moments in the rocket flight process, and finally N rocket modal parameters in the N times of horizontal suspension of the rocket are measured. In the embodiment of the invention, when the modal parameters of the rocket are measured, the bending moment load borne by any selected cabin butt joint surface is close to the bending moment load of actual flight of the rocket, and the modal parameter measurement precision is high. In addition, the rocket in the embodiment of the invention adopts horizontal suspension, so that the requirement on a vertical space is low, the measurement cost is low, and the measurement operation risk is also low.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
Fig. 1 is a flowchart of a rocket modal parameter measurement method according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a rocket modal parameter measurement system according to an embodiment of the present invention;
FIG. 3 is a flowchart of step S3 in FIG. 1 according to an embodiment of the present invention;
in the figure: 1. a frame body; 2. a horizontal suspension assembly; 21. a moving part; 22. a suspending part; 221. a boom; 222. a sling; 223. an elastic suspension member; 224. a force sensor; 3. testing the sensor; 4. an excitation member; 5. a data processing apparatus.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
The embodiment of the invention provides a rocket modal parameter measuring method, which can solve the technical problems of low measuring precision and high measuring cost of the existing rocket modal parameter.
Referring to fig. 1, a rocket modal parameter measuring method includes the following steps:
and step S1, selecting any cabin connecting surface of the rocket, and calculating N bending moments borne by the cabin connecting surface according to the load borne by the N characteristic moments in the rocket flying process. Wherein N is a positive integer.
Specifically, the selected cabin section connecting surface at least comprises a rocket cabin section separating connecting surface and a floating connecting surface, and the rocket cabin section separating connecting surface and the floating connecting surface are generally cabin section connecting surfaces which are weaker in connecting rigidity and have larger influence on the integral modal frequency of the rocket. The N characteristic time selection principles comprise the time corresponding to the maximum bending moment and the minimum bending moment borne by the cabin section connecting surface, other characteristic times can be selected at equal intervals according to flight time, and generally 6-8 characteristic times can be selected.
And step S2, determining N groups of rocket mode test horizontal suspension parameters corresponding to the cabin section connecting surface according to the N bending moments borne by the cabin section connecting surface, wherein the rocket mode test horizontal suspension parameters comprise the number of hoisting points, the positions of the hoisting points and the tension of the hoisting points. And (3) testing horizontal suspension parameters according to 1 group of rocket modes, and after the rocket is horizontally suspended, the bending moment borne by the suspension of the cabin section connecting surface corresponds to the bending moment borne by the cabin section connecting surface at 1 characteristic moment in the rocket flying process. The number of the hoisting points is not less than 3, and 3 or more than 3 hoisting points can more accurately adjust the bending moment borne by the connecting surface of the cabin section, so that the bending moment borne by the connecting surface of the cabin section is closer to that borne in the rocket flying process.
Step S3, horizontally suspending the rocket for N times according to the N groups of rocket modal test horizontal suspension parameters of the cabin section connecting surface, and measuring the rocket modal parameters of the cabin section connecting surface in the N times horizontal suspension state.
Specifically, referring to fig. 3, according to N groups of rocket modal test horizontal suspension parameters of the cabin connection surface, horizontally suspending the rocket N times, and measuring the rocket modal parameters of the cabin connection surface in the state of horizontal suspension N times, the method includes the following steps:
step S301, obtaining the number of lifting points, the positions of the lifting points and the lifting point tension in the kth group of rocket mode test horizontal suspension parameters of the cabin section connecting surface.
Step S302, selecting a corresponding number of horizontal suspension assemblies 2 according to the number of suspension points.
And step S303, moving the selected horizontal suspension component 2 along the frame body 1 according to the lifting point position, and connecting the selected horizontal suspension component 2 with the rocket.
Step S304, the tension of the selected horizontal suspension assembly 2 is adjusted according to the hoisting point tension.
And S305, measuring the rocket modal parameters of the connecting surface of the cabin section in the kth horizontal suspension state. Preferably, a plurality of test sensors 3 are provided on the rocket, and the rocket end is excited using an exciter 4. And acquiring excitation data of the excitation piece 4 and data acquired by the plurality of test sensors 3 after the rocket is excited by using data processing equipment, and calculating and processing to obtain rocket modal parameters of the cabin connecting surface in the kth horizontal suspension state.
In step S306, steps S301 to S305 are repeated so that k is 1,2, …, N, respectively.
The method for measuring the rocket modal parameters in the embodiment of the invention selects a connecting surface of any cabin section of the rocket, determines N groups of rocket modal test horizontal suspension parameters based on the load borne by N characteristic moments in the rocket flight process, horizontally suspends the rocket for N times based on the N groups of rocket modal test horizontal suspension parameters, wherein each time of horizontally suspending the rocket corresponds to the load borne by the connecting surface of the cabin section at the N characteristic moments in the rocket flight process, and finally measures N rocket modal parameters in the N times of horizontally suspending the rocket. In the embodiment of the invention, when the modal parameters of the rocket are measured, the bending moment load borne by any selected cabin butt joint surface is close to the bending moment load of actual flight of the rocket, and the modal parameter measurement precision is high. In addition, the rocket in the embodiment of the invention adopts horizontal suspension, so that the requirement on a vertical space is low, the measurement cost is low, and the measurement operation risk is also low.
The embodiment of the invention also provides a rocket modal parameter measuring system, which comprises: a computing device, a horizontal suspension device and a measuring device.
The calculation device is used for selecting a connection surface of any cabin section of the rocket, and calculating N bending moments borne by the connection surface of the cabin section according to the load borne by N characteristic moments in the rocket flying process; and the device is also used for determining N groups of rocket mode test horizontal suspension parameters corresponding to the cabin section connecting surface according to the N bending moments borne by the cabin section connecting surface, wherein the rocket mode test horizontal suspension parameters comprise the number of hoisting points, the positions of the hoisting points and the tension of the hoisting points.
The horizontal suspension device is used for horizontally suspending the rocket for N times according to N groups of rocket modal test horizontal suspension parameters of the cabin section connecting surface.
The measuring device is used for measuring the rocket modal parameters of the cabin connecting surface in the N-time horizontal suspension state.
The rocket modal parameter measuring system in the embodiment of the invention selects a connecting surface of any cabin section of a rocket, determines N groups of rocket modal test horizontal suspension parameters based on the load borne by N characteristic moments in the rocket flight process, horizontally suspends the rocket for N times based on the N groups of rocket modal test horizontal suspension parameters, wherein each time of horizontally suspending the rocket corresponds to the load borne by the connecting surface of the cabin section at the N characteristic moments in the rocket flight process respectively, and finally measures N rocket modal parameters in N times of horizontally suspending the rocket. In the embodiment of the invention, when the modal parameters of the rocket are measured, the bending moment load borne by any selected cabin butt joint surface is close to the bending moment load of actual flight of the rocket, and the modal parameter measurement precision is high. In addition, the rocket in the embodiment of the invention adopts horizontal suspension, so that the requirement on a vertical space is low, the measurement cost is low, and the measurement operation risk is also low.
As an alternative embodiment, referring to fig. 2, the horizontal suspension device includes: a frame body 1 and a plurality of horizontal suspension assemblies 2.
The plurality of horizontal suspension assemblies 2 are horizontally arranged on the frame body 1 at intervals, each horizontal suspension assembly 2 is provided with a moving part 21 and a suspension part 22, the moving part 21 is arranged on the frame body 1 and can move along the frame body 1, the suspension part 22 is provided with a suspension rod 221 and a suspension belt 222, the upper end of the suspension rod 221 is connected with the moving part 21, the lower end of the suspension rod 221 is connected with one end of the suspension belt 222, and the other end of the suspension belt 222 is used for being connected with a rocket. The moving part 21 can be driven by a servo motor, and has high precision and convenient operation.
Further, the strap 222 is provided in two detachable sections, and a resilient suspension member 223 is provided between the two sections of the strap 222, the resilient suspension member 223 reducing the influence of the strap 222 on the test result during the measurement process. Further, a force sensor 224 is provided on the boom 221, and the tension of the harness 222 can be monitored by the force sensor 224 for adjustment by the worker.
As an alternative embodiment, referring to fig. 2, the measuring device comprises: a plurality of test sensors 3, an exciter 4 and a data processing device 5.
The plurality of test sensors 3 are arranged on the rocket at intervals, the exciting piece 4 is used for exciting the end part of the rocket, and the data processing device 5 is used for acquiring excitation data of the exciting piece 4 and data acquired by the plurality of test sensors 3 after the rocket is excited, and calculating and processing to obtain rocket modal parameters of the connecting surface of the cabin section.
Preferably, the test sensor 3 includes one or more of a strain-type acceleration sensor, a piezoresistive acceleration sensor, and a piezoelectric acceleration sensor. The strain type acceleration sensor, the piezoresistive acceleration sensor and the piezoelectric acceleration sensor are all common modal measurement sensors, and are high in measurement accuracy and low in price.
In the description of the present invention, it should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and operate, and thus, should not be construed as limiting the present invention. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; 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 by those skilled in the art according to specific situations.
It is to be noted that, in the present invention, relational terms such as "first" and "second", and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
The foregoing are merely exemplary embodiments of the present invention, which enable those skilled in the art to understand or practice the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A rocket modal parameter measuring method is characterized by comprising the following steps:
selecting any cabin connecting surface of the rocket, and calculating N bending moments borne by the cabin connecting surface according to the load borne by the rocket at N characteristic moments in the flying process;
determining N groups of rocket mode test horizontal suspension parameters corresponding to the cabin section connecting surface according to the magnitude of N bending moments borne by the cabin section connecting surface, wherein the rocket mode test horizontal suspension parameters comprise the number of hoisting points, the positions of the hoisting points and the tension of the hoisting points;
and horizontally suspending the rocket for N times according to the N groups of rocket modal test horizontal suspension parameters of the cabin section connecting surface, and measuring the rocket modal parameters of the cabin section connecting surface in the N times of horizontal suspension state.
2. A rocket modal parameter measuring method according to claim 1, wherein said horizontally suspending a rocket for N times according to N groups of rocket modal test horizontal suspension parameters of the cabin connection surface, and measuring rocket modal parameters of the cabin connection surface in N horizontally suspended states, comprises the steps of:
step S301, acquiring the number of hoisting points, the positions of the hoisting points and the hoisting point tension in the kth group of rocket mode test horizontal suspension parameters of the cabin section connecting surface;
step S302, selecting a corresponding number of horizontal suspension assemblies (2) according to the number of the suspension points;
step S303, moving the selected horizontal suspension component (2) along the frame body (1) according to the position of the lifting point, and connecting the selected horizontal suspension component (2) with the rocket;
step S304, adjusting the tension of the selected horizontal suspension assembly (2) according to the tension of the suspension point;
step S305, measuring rocket modal parameters of the cabin section connecting surface in the kth horizontal suspension state;
in step S306, steps S301 to S305 are repeated so that k is 1,2, …, N, respectively.
3. A rocket modal parameter measuring method according to claim 2, wherein said measuring the rocket modal parameter of the cabin attachment plane in the kth horizontal suspension state comprises the steps of:
arranging a plurality of test sensors (3) on the rocket, and exciting the end part of the rocket by using an exciting piece (4);
and (3) acquiring excitation data of the excitation piece (4) and data acquired by the plurality of test sensors (3) after the rocket is excited by using data processing equipment (5), and calculating and processing to obtain rocket modal parameters of the cabin connecting surface in the kth horizontal suspension state.
4. A rocket modal parameter measuring method as recited in claim 1, wherein: the cabin connecting surface at least comprises a rocket cabin separation connecting surface and a floating connecting surface.
5. A rocket modal parameter measurement system, comprising:
the computing device is used for selecting any cabin connecting surface of the rocket and computing N bending moments borne by the cabin connecting surface according to the load borne by the N characteristic moments in the rocket flying process; the system is also used for determining N groups of rocket mode test horizontal suspension parameters corresponding to the cabin section connecting surface according to the N bending moments borne by the cabin section connecting surface, wherein the rocket mode test horizontal suspension parameters comprise the number of hoisting points, the positions of the hoisting points and the tension of the hoisting points;
the horizontal suspension device is used for horizontally suspending the rocket for N times according to the N groups of rocket modal test horizontal suspension parameters of the cabin section connecting surface;
and the measuring device is used for measuring the rocket modal parameters of the cabin section connecting surface in the N-time horizontal suspension state.
6. A rocket modal parameter measuring system as recited in claim 5, wherein said horizontal suspension means comprises:
a frame body (1);
the rocket comprises a plurality of horizontal suspension assemblies (2), wherein the horizontal suspension assemblies (2) are horizontally arranged on a frame body (1) at intervals, each horizontal suspension assembly (2) is provided with a moving part (21) and a suspension part (22), the moving part (21) is arranged on the frame body (1) and can move along the frame body (1), the suspension part (22) is provided with a suspension rod (221) and a suspension strap (222), the upper end of the suspension rod (221) is connected with the moving part (21), the lower end of the suspension rod is connected with one end of the suspension strap (222), and the other end of the suspension strap (222) is used for being connected with a rocket.
7. A rocket modal parameter measuring system as recited in claim 6, wherein:
the hanging strip (222) is two detachable sections, and an elastic hanging piece (223) is arranged between the two sections of the hanging strip (222).
8. A rocket modal parameter measuring system as recited in claim 6, wherein: a force sensor (224) is arranged on the suspension rod (221).
9. A rocket modal parameter measuring system as recited in claim 7, wherein said measuring means comprises:
a plurality of test sensors (3) which are arranged on the rocket at intervals;
an exciter (4) for exciting an end of the rocket;
and the data processing device (5) is used for acquiring excitation data of the excitation piece (4) and data acquired by the plurality of test sensors (3) after the rocket is excited, and calculating and processing to obtain rocket modal parameters of the cabin section connecting surface.
10. A rocket modal parameter measuring system as recited in claim 9, wherein:
the test sensor (3) comprises one or more of a strain type acceleration sensor, a piezoresistive type acceleration sensor and a piezoelectric type acceleration sensor.
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| CN202110126141.8A CN112906129A (en) | 2021-01-29 | 2021-01-29 | Rocket modal parameter measuring method and system |
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| CN208964389U (en) * | 2018-10-30 | 2019-06-11 | 北京电子工程总体研究所 | A kind of adjustable horizontal suspension device in orientation |
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