CN114251411A - Active section vibration reduction structure of coaxial double-reflection space optical remote sensor - Google Patents
Active section vibration reduction structure of coaxial double-reflection space optical remote sensor Download PDFInfo
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- CN114251411A CN114251411A CN202010994125.6A CN202010994125A CN114251411A CN 114251411 A CN114251411 A CN 114251411A CN 202010994125 A CN202010994125 A CN 202010994125A CN 114251411 A CN114251411 A CN 114251411A
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- remote sensor
- space optical
- optical remote
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/022—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using dampers and springs in combination
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/08—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with rubber springs ; with springs made of rubber and metal
- F16F15/085—Use of both rubber and metal springs
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F2222/00—Special physical effects, e.g. nature of damping effects
- F16F2222/04—Friction
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F2224/00—Materials; Material properties
- F16F2224/02—Materials; Material properties solids
- F16F2224/0225—Cellular, e.g. microcellular foam
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F2228/00—Functional characteristics, e.g. variability, frequency-dependence
- F16F2228/04—Frequency effects
Abstract
The invention discloses an active section vibration damping structure of a novel coaxial double-reflection space optical remote sensor, which comprises three flexible supporting legs assembled at the bottom of the space optical remote sensor, wherein the three flexible supporting legs are uniformly distributed along the circumferential direction of the space optical remote sensor; the upper end of the flexible leg is configured to connect to a platform; the damping element is assembled on the connecting platform of the flexible leg and connected with the flexible leg through a screw; the flexible supporting legs are assembled and fixed with the space optical remote sensor through screws; the damping element is a metal rubber damping element. The vibration reduction structure adopts Bipod flexible supporting legs made of titanium alloy TC4 to support the bottom of the space optical remote sensor, and simultaneously, each flexible supporting leg is integrated with eight damping elements, the flexible supporting legs and the damping elements are arranged right below a truss embedded part of the main bearing chamber, so that the rigidity of the space optical remote sensor is increased, and meanwhile, the natural frequency of the space optical remote sensor is increased and is far away from the natural frequency of a satellite.
Description
Technical Field
The invention relates to the technical field of space remote sensors, in particular to an active section vibration reduction structure of a coaxial double-reflection space optical remote sensor.
Background
The space optical remote sensor needs to experience various environmental conditions in ground environmental tests and space use, a rocket engine can cause random vibration in a rocket launching stage, the frequency is 10-2000 Hz, structural deformation and micro stress enable optical elements to generate maladjustment and surface type errors, accordingly, the imaging quality of an optical system is reduced, and vibration can also cause failure of internal elements of the space remote sensor. Therefore, the development of an active section vibration reduction structure of the space optical remote sensor to reduce the influence of vibration caused by carrying during rocket launching on the space optical remote sensor is of great significance.
Disclosure of Invention
The invention provides a vibration reduction structure which has simple structure, convenient assembly, light weight and small volume and is suitable for severe environment so as to improve the vibration resistance of a space optical remote sensor, and the vibration reduction structure can ensure that the random vibration response value RMS is less than 2g in all directions and ensure that the first-order natural frequency is more than 110 Hz.
In order to achieve the above purpose, the invention provides the following technical scheme:
the invention relates to an active section vibration reduction structure of a coaxial double-reflection space optical remote sensor, which is integrated at the lower part of the space optical remote sensor and comprises:
the number of the flexible supporting legs is three, and the three flexible supporting legs are uniformly distributed along the circumferential direction of the space optical remote sensor;
the upper end of the flexible leg is configured to connect to a platform;
the connecting platform of the flexible leg is provided with a damping element, and the damping element is connected with the flexible leg through a screw;
the flexible supporting leg is fixedly assembled with the space optical remote sensor through the screw;
the damping element is a metal rubber damping element.
Furthermore, the flexible support leg adopts a Bipod flexible support leg;
the flexible leg includes:
the landing leg body is provided with two symmetrically arranged landing leg parts; and
the connecting platform is formed at the upper end of the leg part and is integrally formed with the leg part;
the connecting platform is of a quadrilateral structure;
the flexible supporting legs are made of titanium alloy TC 4;
four groups of damping elements are uniformly distributed on the connecting platform along the circumferential direction of the connecting platform, and each group of damping elements comprises two damping elements.
Furthermore, a plurality of hollowed holes are processed on the leg portion, and the leg portion is formed into a lightweight structure by processing the plurality of hollowed holes.
Furthermore, the connecting platform is provided with a mounting hole;
the mounting hole includes:
first holes formed at both ends of the mounting hole; and
a second hole coaxial with the first holes and formed between the two first holes;
the first hole has an opening size larger than that of the second hole;
a sleeve cup is embedded in the first hole, and one end part of the sleeve cup, which is close to the second hole, is embedded in the second hole to form an embedding structure;
the sleeve cup is provided with an embedded groove, the damping element is embedded into the embedded groove, and a gasket is arranged on one side of the damping element, which is far away from the sleeve cup;
the gasket, the damping element and the sleeve cup are all connected through the screw in a fastening mode.
Further, a truss embedded part is integrated on the upper part of the space optical remote sensor;
the bottom of the space optical remote sensor is provided with a threaded hole matched with the damping element;
the flexible supporting leg is assembled in the threaded hole through the screw and the space optical remote sensor.
Furthermore, a certain gap is reserved between the connecting platform of the flexible supporting leg and the space optical remote sensor.
In the technical scheme, the active section vibration reduction structure of the coaxial double-reflection space optical remote sensor provided by the invention has the following beneficial effects:
the vibration reduction structure adopts Bipod flexible supporting legs made of titanium alloy TC4 to support the bottom of the space optical remote sensor, and simultaneously, each flexible supporting leg is integrated with eight damping elements, the flexible supporting legs and the damping elements are arranged right below a truss embedded part of the main bearing chamber, so that the rigidity of the space optical remote sensor is increased, and meanwhile, the natural frequency of the space optical remote sensor is increased and is far away from the natural frequency of a satellite.
The active section vibration reduction structure of the coaxial double-reflection space optical remote sensor ensures that the first-order natural frequency of the whole structure of the space optical remote sensor is greater than 110Hz and is far away from the first-order natural frequency of a satellite, avoids resonance and can ensure that the random vibration response value RMS of the space optical remote sensor is less than 2 g.
The vibration damping structure has the advantages of high rigidity, simple structure, light weight, simple assembly and good vibration damping effect, the active section vibration damping structure of the space optical remote sensor cannot be aged, the service life cannot be influenced by space irradiation, and the vibration damping structure is suitable for the space environment with space irradiation and frequent high-low temperature replacement.
Drawings
In order to more clearly illustrate the embodiments of the present application or technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments described in the present invention, and other drawings can be obtained by those skilled in the art according to the drawings.
Fig. 1 is a first structural schematic diagram of an active segment damping structure of a coaxial dual-reflection space optical remote sensor and an assembly state of the space optical remote sensor according to an embodiment of the present invention;
fig. 2 is a structural schematic diagram ii of an active segment damping structure of a coaxial dual-reflection space optical remote sensor and an assembly state of the space optical remote sensor according to an embodiment of the present invention;
fig. 3 is a structural schematic diagram three of an active segment damping structure of a coaxial dual-reflection space optical remote sensor and an assembly state of the space optical remote sensor according to an embodiment of the present invention;
fig. 4 is a first structural schematic diagram of an active section damping structure of a coaxial dual-reflection spatial optical remote sensor according to an embodiment of the present invention;
fig. 5 is a schematic structural diagram of a damping structure of an active section of a coaxial dual-reflection spatial optical remote sensor according to an embodiment of the present invention.
Description of reference numerals:
1. a spatial optical remote sensor; 2. embedding the truss; 3. a flexible leg;
301. a leg portion; 302. connecting the platform; 303. mounting holes; 304. hollowing out holes;
401. a screw; 402. a gasket; 403. a damping element; 404. sleeving a cup;
30301. a first hole; 30302. a second aperture.
Detailed Description
In order to make the technical solutions of the present invention better understood, those skilled in the art will now describe the present invention in further detail with reference to the accompanying drawings.
As shown in fig. 1 to 5;
the invention relates to an active section vibration reduction structure of a coaxial double-reflection space optical remote sensor, which is integrated at the lower part of a space optical remote sensor 1 and comprises the following components:
the flexible support legs 3 are assembled at the bottom of the space optical remote sensor 1, the number of the flexible support legs 3 is three, and the three flexible support legs 3 are uniformly distributed along the circumferential direction of the space optical remote sensor 1;
the upper end of the flexible leg 3 is configured to connect to a platform 302;
the connection platform 302 of the flexible leg 3 is equipped with a damping element 403, and the damping element 403 is connected with the flexible leg 3 by means of screws 401;
the flexible leg 3 is fixedly assembled with the space optical remote sensor 1 through a screw 401;
the damping element 403 is a metal rubber damping element.
Specifically, the embodiment discloses a novel active section vibration damping structure of a coaxial dual-reflection space optical remote sensor 1, which is assembled at the bottom of the space optical remote sensor 1, and meanwhile, the vibration damping structure comprises a flexible leg 3 and a damping element 403 integrated in the flexible leg 3. The flexible leg 3 is fixed to the space optical remote sensor 1 by the connecting platform 302 at the upper end thereof, and the damping element 403 disclosed in this embodiment is a metal rubber damping element. The selection of the shock absorber in the aerospace field is particularly strict, the space optical remote sensor 1 bears periodic high and low temperature and space radiation environment when in on-orbit operation, the requirement on the material of the shock absorber is high, common rubber materials are not suitable, metal rubber resists high and low temperature, resists corrosion, is not easy to age and resist impact, has long service life, can be used in severe environment, can absorb shock in a wider frequency band, and can soften the rigidity of the metal rubber when large excitation is applied, thereby playing a role in changing the inherent frequency of the structure and avoiding the generation of resonance. Based on the dry friction hysteresis damping characteristic of the metal rubber, the metal rubber is widely applied to the aerospace field and can be used as a vibration damping material of a space optical remote sensor.
The metal rubber material is a porous structural material with dry friction damping, and is prepared by winding, stretching, weaving, molding and other technological processes of metal wires. The metal rubber material dissipates vibration energy due to dry friction damping generated by relative sliding between the metal wire layers in the metal rubber material, so that the vibration isolation effect is achieved. The metal rubber material is used as a porous homogeneous material, can adapt to environments with different temperatures, different humidity and the like, and solves the problem of vibration reduction under complex working conditions. However, a single metal rubber shock absorber has asymmetric elasticity, and due to the influence of viscous damping force and the restoring force of double fold lines, the mechanical property of the shock absorber is more easily unstable, so that the metal rubber shock absorber is difficult to achieve ideal dynamic performance, therefore, the shock absorber of the space optical remote sensor 1 adopts a series connection mode of two metal rubbers, the performances of an upper metal rubber shock absorbing element and a lower metal rubber shock absorbing element are consistent, and meanwhile, the stable shock absorbing performance is obtained, and the tension and compression of the upper shock absorbing element and the lower shock absorbing element are consistent.
Preferably, the flexible leg 3 in this embodiment is a Bipod flexible leg;
the flexible leg 3 includes:
the landing leg comprises a landing leg body, wherein the landing leg body is provided with two landing leg parts 301 which are symmetrically arranged; and
a connecting platform 302 formed at the upper end of the leg portion 301 and integrally formed with the leg portion 301;
the connecting platform 302 is in a quadrilateral structure;
the flexible supporting leg 3 is made of titanium alloy TC 4;
the connecting platform 302 has four sets of damping elements 403 distributed along its circumference, each set of damping elements 403 including two damping elements 403.
The flexible landing leg 3 disclosed in this embodiment directly selects for use the flexible landing leg of Bipod, two landing leg structures promptly, and in order to satisfy the rigidity requirement, the material of flexible landing leg 3 selects for use titanium alloy TC4 material.
Meanwhile, in order to satisfy the design requirement of light weight, a plurality of hollow holes 304 are formed in the leg portion 301, and the leg portion 301 is formed into a light weight structure by processing the plurality of hollow holes 304.
Preferably, in this embodiment, the connecting platform 302 is provided with a mounting hole 303;
the mounting hole 303 includes:
a first hole 30301 formed at both ends of the mounting hole 303; and
a second bore 30302 coaxial with the first bores 30301 and formed between the two first bores 30301;
the open pore size of the first pores 30301 is greater than the open pore size of the second pores 30302;
a sleeve cup 404 is embedded in the first hole 30301, and one end part of the sleeve cup 404 close to the second hole 30302 is embedded in the second hole 30302 to form a scarf joint structure;
the sleeve cup 404 is provided with an embedded groove, the damping element 403 is embedded into the embedded groove, and the gasket 402 is arranged on one side of the damping element 403 far away from the sleeve cup 404;
wherein the gasket 402, the damping element 403 and the sleeve cup 404 are all fastened and connected by screws 401.
Preferably, a truss embedded part 2 is integrated on the upper part of the space optical remote sensor 1 in the embodiment;
the bottom of the space optical remote sensor 1 is provided with a threaded hole matched with the damping element 403;
the flexible leg 3 is assembled with the space optical remote sensor 1 in the threaded hole by a screw 401.
Preferably, a certain gap is reserved between the connecting platform 302 of the flexible leg 3 and the space optical remote sensor 1 in the embodiment.
The damping element 403 disclosed in this embodiment is a hollow circular cylinder, and is assembled in an embedded groove on the inner side of the sleeve cup 404, the side surface of the metal rubber damping element and the ground are attached to the sleeve cup 404, the side surface which is not in contact with the sleeve cup 404 is in contact with the space optical remote sensor 1 through the gasket 402, the metal rubber damping element is filled in the sleeve cup 404 in an initial state without stress, and when a satellite vibrates, the vibration causes the space optical remote sensor 1 to shift along each direction, so that the metal rubber damping element deforms and suppresses the vibration of the space optical remote sensor 1.
The vibration reduction structure of the embodiment adopts a series structure of two metal rubber damping elements to separate the metal rubber damping element at the upper side from the metal rubber damping element at the lower side, and the metal rubber damping elements at the upper side and the lower side deform under stress respectively, so that the working efficiency of the vibration absorber is improved.
The porosity and shape of the metal rubber are derived from the support damping required by the active section vibration damping structure of the coaxial two-reflection space optical remote sensor 1.
When the damping device works, when a rocket engine causes random vibration in the process of lifting off a rocket, the vibration is transmitted to the damping element 403 through the flexible supporting legs 3 connected with the satellite body, so that the damping element 403 generates elastic deformation, the vibration energy is consumed, the vibration of the space optical remote sensor 1 is inhibited, and the metal rubber has good damping performance and stable supporting rigidity.
In the technical scheme, the active section vibration reduction structure of the coaxial double-reflection space optical remote sensor provided by the invention has the following beneficial effects:
the vibration reduction structure of the invention adopts Bipod flexible supporting legs made of titanium alloy TC4 material to support the bottom of the space optical remote sensor 1, simultaneously, each flexible supporting leg 3 integrates eight damping elements 403, the flexible supporting legs 3 and the damping elements 403 are arranged right below the truss embedded part 2 of the main bearing chamber, the rigidity of the space optical remote sensor 1 is increased, and simultaneously, the natural frequency of the space optical remote sensor 1 is also increased and is far away from the natural frequency of a satellite.
The active section vibration reduction structure of the coaxial two-reflection space optical remote sensor 1 ensures that the first-order natural frequency of the whole structure of the space optical remote sensor 1 is greater than 110Hz and is far away from the first-order natural frequency of a satellite, avoids resonance and can ensure that the random vibration response value RMS of the space optical remote sensor 1 is less than 2 g.
The vibration damping structure has the advantages of high rigidity, simple structure, light weight, simple assembly and good vibration damping effect, the active section vibration damping structure of the space optical remote sensor 1 cannot be aged, the service life cannot be influenced by space irradiation, and the vibration damping structure is suitable for the space environment with space radiation and frequent high-low temperature replacement.
While certain exemplary embodiments of the present invention have been described above by way of illustration only, it will be apparent to those of ordinary skill in the art that the described embodiments may be modified in various different ways without departing from the spirit and scope of the invention. Accordingly, the drawings and description are illustrative in nature and should not be construed as limiting the scope of the invention.
Claims (6)
1. An active section damping structure of a coaxial dual-reflection space optical remote sensor, which is integrated in the lower part of the space optical remote sensor (1), characterized in that the damping structure comprises:
the flexible support legs (3) are assembled at the bottom of the space optical remote sensor (1), the number of the flexible support legs (3) is three, and the three flexible support legs (3) are uniformly distributed along the circumferential direction of the space optical remote sensor (1);
the upper end of the flexible leg (3) is configured to be connected to a platform (302);
the connection platform (302) of the flexible leg (3) is equipped with a damping element (403), and the damping element (403) is connected with the flexible leg (3) by a screw (401);
the flexible leg (3) is fixedly assembled with the space optical remote sensor (1) through the screw (401);
the damping element (403) is a metal rubber damping element.
2. The active section damping structure of a coaxial double-reaction space optical remote sensor according to claim 1, characterized in that the flexible leg (3) is a Bipod flexible leg;
the flexible leg (3) comprises:
a leg body having two leg portions (301) arranged symmetrically; and
the connecting platform (302) is formed at the upper end of the leg part (301) and is integrally formed with the leg part (301);
the connecting platform (302) is of a quadrilateral structure;
the flexible supporting leg (3) is made of titanium alloy TC 4;
four groups of damping elements (403) are uniformly distributed on the connecting platform (302) along the circumferential direction of the connecting platform, and each group of damping elements (403) comprises two damping elements (403).
3. The active section damping structure of the coaxial double-reflector space optical remote sensor according to claim 2, wherein a plurality of hollowed holes (304) are formed in the leg portion (301), and the leg portion (301) is formed into a lightweight structure by machining the plurality of hollowed holes (304).
4. The active section damping structure of a coaxial double-reaction space optical remote sensor according to claim 2, wherein the connecting platform (302) is provided with a mounting hole (303);
the mounting hole (303) includes:
a first hole (30301) formed at both ends of the mounting hole (303); and
a second bore (30302) coaxial with said first bores (30301) and formed between two of said first bores (30301);
the open pore size of the first pores (30301) is greater than the open pore size of the second pores (30302);
a sleeve cup (404) is embedded in the first hole (30301), and one end part of the sleeve cup (404) close to the second hole (30302) is embedded in the second hole (30302) to form a scarf joint structure;
the sleeve cup (404) is provided with an embedded groove, the damping element (403) is embedded into the embedded groove, and a gasket (402) is installed on one side, away from the sleeve cup (404), of the damping element (403);
the gasket (402), the damping element (403) and the sleeve cup (404) are all fixedly connected through the screw (401).
5. The active section damping structure of the coaxial double-reaction space optical remote sensor according to claim 4, characterized in that a truss embedded part (2) is integrated on the upper part of the space optical remote sensor (1);
the bottom of the space optical remote sensor (1) is provided with a threaded hole matched with the damping element (4403);
the flexible supporting leg (3) is assembled in the threaded hole through the screw (401) and the space optical remote sensor (1).
6. The active section damping structure of the coaxial double-reaction space optical remote sensor according to claim 5, characterized in that a certain gap is reserved between the connecting platform (302) of the flexible leg (3) and the space optical remote sensor (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010994125.6A CN114251411A (en) | 2020-09-21 | 2020-09-21 | Active section vibration reduction structure of coaxial double-reflection space optical remote sensor |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010994125.6A CN114251411A (en) | 2020-09-21 | 2020-09-21 | Active section vibration reduction structure of coaxial double-reflection space optical remote sensor |
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