CN107939905A - A kind of satellite and the rocket adaptive device for micro-nano satellite vibration damping - Google Patents
A kind of satellite and the rocket adaptive device for micro-nano satellite vibration damping Download PDFInfo
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- CN107939905A CN107939905A CN201711155203.8A CN201711155203A CN107939905A CN 107939905 A CN107939905 A CN 107939905A CN 201711155203 A CN201711155203 A CN 201711155203A CN 107939905 A CN107939905 A CN 107939905A
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- 238000013016 damping Methods 0.000 title claims abstract description 60
- 230000003044 adaptive effect Effects 0.000 title claims abstract description 21
- 230000000903 blocking effect Effects 0.000 claims abstract description 157
- 238000012360 testing method Methods 0.000 claims abstract description 30
- 230000006978 adaptation Effects 0.000 claims abstract description 25
- 238000013461 design Methods 0.000 claims abstract description 15
- 238000004458 analytical method Methods 0.000 claims abstract description 8
- 238000004088 simulation Methods 0.000 claims abstract description 7
- 238000002474 experimental method Methods 0.000 claims description 11
- 238000000034 method Methods 0.000 claims description 11
- 238000002955 isolation Methods 0.000 claims description 8
- 238000006073 displacement reaction Methods 0.000 claims description 7
- 230000008569 process Effects 0.000 claims description 5
- 230000003068 static effect Effects 0.000 claims description 5
- 230000003321 amplification Effects 0.000 claims description 4
- 230000008878 coupling Effects 0.000 claims description 4
- 238000010168 coupling process Methods 0.000 claims description 4
- 238000005859 coupling reaction Methods 0.000 claims description 4
- 238000003199 nucleic acid amplification method Methods 0.000 claims description 4
- 238000004080 punching Methods 0.000 claims description 4
- 230000004044 response Effects 0.000 claims description 4
- 238000007873 sieving Methods 0.000 claims description 4
- 238000001228 spectrum Methods 0.000 claims description 4
- PRPINYUDVPFIRX-UHFFFAOYSA-N 1-naphthaleneacetic acid Chemical compound C1=CC=C2C(CC(=O)O)=CC=CC2=C1 PRPINYUDVPFIRX-UHFFFAOYSA-N 0.000 claims description 3
- 230000003139 buffering effect Effects 0.000 claims description 3
- WQAQPCDUOCURKW-UHFFFAOYSA-N butanethiol Chemical compound CCCCS WQAQPCDUOCURKW-UHFFFAOYSA-N 0.000 claims description 3
- 238000004364 calculation method Methods 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 3
- 230000010355 oscillation Effects 0.000 claims description 3
- 238000012216 screening Methods 0.000 claims description 3
- 229920001967 Metal rubber Polymers 0.000 claims description 2
- 235000006508 Nelumbo nucifera Nutrition 0.000 claims description 2
- 240000002853 Nelumbo nucifera Species 0.000 claims description 2
- 235000006510 Nelumbo pentapetala Nutrition 0.000 claims description 2
- 239000000463 material Substances 0.000 claims description 2
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Classifications
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/228—Damping of high-frequency vibration effects on spacecraft elements, e.g. by using acoustic vibration dampers
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
Abstract
The invention discloses a kind of satellite and the rocket adaptive device for micro-nano satellite vibration damping, satellite and the rocket mechanical interface adaptation and satellite system irrespective of size vibration damping are carried out integrated design by the present invention, suitable for the satellite and the rocket adaptive device of 1kg~50kg grades of micro-nano satellite vibration dampings, it can meet that the micro-nano satellite unlocking mechanism of annulus configuration is adapted to the connection of rocket body stent, but also with good damping property and shock resistance, to be effectively improved the mechanical environment of micro-nano satellite transmitter section；Meanwhile the present invention has formulated the complete simulation analysis of set of system and checking test flow for the preferred of its up/down cushion blocking proper stiffness, for the preferred of cushion blocking rigidity, to adapt to the requirement of the particular surroundings of AEROSPACE APPLICATION.
Description
Technical field
The present invention relates to a kind of satellite and the rocket adaptive device with vibration damping, particularly one kind to be used for 1kg~50kg grades of micro-nano satellites
The satellite and the rocket adaptive device of vibration damping.
Background technology
Satellite subtracts/and vibration isolation technique is always of interest for various countries' aerospace engineering circle, at present both at home and abroad with regard to whole star vibration isolator technology
Carry out a series of researchs in succession, include active control, passive type control and active-passive integratedization control etc., part
Achievement in research has had the engineer application of actual transmission.At present in country's space industry, mainly take passive type vibration isolation and answer
During Payload Attach Fitting for primary improves, preferable effectiveness in vibration suppression is achieved.But for the micro-nano satellite vibration damping of lift-launch
In terms of research and the development of micro-nano satellite vibration damping adapter apparatus, still lack correlative study and application experience.With micro-nano satellite
Flourish, the satellite and the rocket interface of micro-nano satellite also gradually tends to standardize, and the Payload Attach Fitting for micro-nano satellite vibration damping is ground
The ripe of hair, and it is imperative.
At present, the typical satellite and the rocket mechanical interface of domestic micro-nano satellite is in same plane, four side equidistantly distributed of rectangle
8~12 M6 connecting holes, pitch-row is in 80mm~100mm, and the rectangle length of side is in 200mm~300mm (generally square).It is and micro-
Nano satellite separates the various informative of unlock, and the unlocking mechanism engineer application of the annulus configuration of its miniaturization is more.Micro-nano satellite
Vibration damping adaptive device stills need to meet that micro-nano satellite separating mechanism lower end frame is adapted to the connection of rocket body stent on mechanical interface
It is required that.
Satellite will undergo the sound and vibration mechanical environment of complexity in transmitter section, bear a variety of Different Dynamics from carrier rocket and carry
Lotus.To reduce launch cost, micro-nano satellite is launched usually as Process of Piggyback Satellite, and passing of satelline Payload Attach Fitting and carrier rocket are taken
Carry stent connection.Traditional micro-nano satellite adapter, rigidity is big, and damping is weak, and dynamic response amplification is notable, causes directly to pass through
Payload Attach Fitting is delivered to several times of its environmental load magnitude of satellite usually above primary.
The content of the invention
The technology of the present invention solves the problems, such as：Asked for the mechanical interface adaptation that the whole star vibration damping of micro-nano satellite and the satellite and the rocket connect
Topic, it is proposed that a kind of integrated design, satellite and the rocket adaptive device suitable for 1kg~50kg grade micro-nano satellite vibration dampings, you can expire
The micro-nano satellite unlocking mechanism of sufficient annulus configuration is adapted to the connection of rocket body stent, but also with good damping property and shock resistance
Performance, to be effectively improved the mechanical environment of micro-nano satellite transmitter section.
The present invention technical solution be：
A kind of satellite and the rocket adaptive device for micro-nano satellite vibration damping, including star end adaptation frame, cushion blocking center limited post, on
Stop collar flange, lower end cushion blocking and arrow end adaptation frame, star end adaptation frame subtract with circumferentially distributed on the outside of end cushion blocking, cushion blocking
The pad outside stop collar flange that shakes rigidly consolidates, and is adapted to frame by upper end cushion blocking, lower end cushion blocking with arrow end and is connected, and upper end subtracts
Shake pad, lower end cushion blocking is embedded on the outside of cushion blocking in stop collar flange, is constrained centrally through cushion blocking center limited post；
Upper end cushion blocking and the selection of lower end cushion blocking meet the cushion blocking of satellite dynamic load requirement；
Arrow end is adapted to frame and is rigidly connected with delivery Process of Piggyback Satellite stent, is suitable for satellite and the rocket interface；Star end adaptation frame is defended with micro-nano
Star installation interface is rigidly connected, and is suitable for satellite mounting surface interface.
The quantity of stop collar flange accepts or rejects preferably 12 points carryings and 8 points of carryings according to bearing capacity demand on the outside of cushion blocking.
Upper end cushion blocking and lower end cushion blocking use metal rubber material, are hollow cylinder configuration.
The inside cylindrical face of upper end cushion blocking and lower end cushion blocking and the face of cushion blocking center limited post completely attach to, outside
Cylinder is then completely attached to stop collar flange medial surface on the outside of cushion blocking, forms radial constraint, to realize to satellite oscillation crosswise
Or damping of shocks vibration isolation.
The anchor ring up and down of upper cushion blocking is embedded in the spacing post head round recessed in cushion blocking center and outside cushion blocking respectively
On the stop collar flange of side in round recessed, the anchor ring up and down of lower cushion blocking is embedded on the outside of cushion blocking circle under stop collar flange respectively
In the groove of in groove and arrow end adaptation frame upper surface.
The vibration in three rotational freedom directions of satellite is adapted to frame and cushion blocking stop collar integrated flange knot by star end
Structure is converted into cushion blocking and axially or radially vibrates.
Upper end cushion blocking (3) and lower end cushion blocking (5) selection meet satellite dynamic load requirement cushion blocking method for：
(1) delivery ICD interfaces and design of satellites scheme are determined；
(2) the mechanics interface condition according to satellite gross mass with delivery to satellite, including whole star rigidity condition, Static Design
Load, low frequency sinusoidal vibration condition, high frequency random vibration condition and impact condition, are converted to the requirement for bearing capacity of cushion blocking, just
The cushion blocking of proper stiffness scope and quantity is selected, calculation formula is as follows：
In formula,The respectively minimum rigidity value of cushion blocking vertical and horizontal, primary election cushion blocking rigidity should not
Less than the minimum rigidity value；WithRespectively cushion blocking vertical and horizontal allow maximum displacement；M and HcRespectively satellite
Quality and height of center of mass；Amax=max { rAsin,3Arand, AsinFor satellite sinusoidal vibration condition peak accelerator,For satellite random vibration condition peak accelerator, P (f) is random vibration test condition power spectrum
Spend function；Dynamics amplification coefficient when r is satellite sinusoidal vibration at barycenter with respect to satellite and the rocket interface；R is damper distribution circle half
Footpath；N is damper distributed quantity；θiFor i-th of damper position angle, damper installation center point is defined as with being distributed in circle
The line of heart point, the angle between the line and direction of vibration axis；I numbers for damper, on definition vibration direction of principal axis in distance
The farthest damper numbering of heart point is 1；
(3) experimental test is carried out for the rigidity of primary election cushion blocking, its BUSH is created according to the test value of cushion blocking rigidity
Finite element unit, is combined the analysis of body coupling Simulation with reference to whole star finite element model, obtains satellite fundamental frequency ωa, according to following
Formula determines the cushion blocking rigidity for meeting condition, participates in next step experiment sieving：
ωa≥κωmin
In formula, ωminLower limit is required for whole star rigidity condition, κ is safety coefficient；
(4) mechanical structure of satellite is combined, and is rejected using feature level scan test and does not meet subtracting for whole star rigidity requirement
Shake pad, i.e. experiment obtains satellite fundamental frequency ωtMeet ωt≥ωmin；Further, impact, sinusoidal vibration and random vibration test are utilized
Data verification cushion blocking bearing capacity and the damping efficiency for determining each state cushion blocking, i.e.,：
In formula,WithRespectively expire magnitude vibration experiment before and after test and measure satellite fundamental frequency, ηiFor i-th of damper
The damping efficiency of test specimen, L are damper testpieces number,WithRespectively satellite is with vibration damping i and without vibration damping i
Dynamic response peak accelerator value, according to above-mentioned formula, rejecting cannot meet that satellite rigidity and dynamic load transmission will
Cushion blocking ask or relatively low damping efficiency, takes maximum ηiCushion blocking rigidity be preferred result.
Step 3 increases the cushion blocking of corresponding rigidity in the positive and negative scope of proper stiffness value for analyzing selection, tests as a comparison
Part, cushion blocking testpieces rigidity upper limit value are calculated according to equation below：
In formula,The respectively maximum rigidity value upper limit of cushion blocking vertical and horizontal, primary election cushion blocking rigidity
Should without departing from the upper limit value,WithRespectively cushion blocking vertical and horizontal allow least displacement, cushion blocking testpieces rigidity
Lower limit can less thanWithSelected within the 10% of calculated value, finally complete the wheel sieve of cushion blocking second according to step 4
Choosing, determines the optimal rigidity of cushion blocking testpieces.
In step 2, takeWithFor 2.5mm, r values are 5, f0Experience value is 200Hz~300Hz.
The present invention compared with prior art the advantages of be：
(1) present invention by the satellite and the rocket mechanical interface adaptation and satellite system irrespective of size vibration damping carry out integrated design, suitable for 1kg~
The satellite and the rocket adaptive device of 50kg grades of micro-nano satellite vibration dampings, you can meet the micro-nano satellite unlocking mechanism and rocket body stent of annulus configuration
Connection adaptation, but also with good damping property and shock resistance, to be effectively improved the mechanical ring of micro-nano satellite transmitter section
Border；
(2) structure size of the invention is small, light-weight, good rigidity, whole star envelope size is influenced it is small, and can be with type spectrum
Change；
(3) present invention for its up/down cushion blocking proper stiffness it is preferred formulated the complete simulation analysis of set of system and
Checking test flow, for the preferred of cushion blocking rigidity, to adapt to the requirement of the particular surroundings of AEROSPACE APPLICATION.
Brief description of the drawings
Fig. 1 is the monnolithic case schematic diagram of present invention carrying 30kg~50kg；
Fig. 2 is the overall cut-away illustration of the present invention；
Fig. 3 is the monnolithic case schematic diagram of present invention carrying 1kg~30kg；
Fig. 4 is decomposing state overall schematic of the present invention；
Fig. 5 is cushion blocking rigidity preferred flow schematic diagram of the present invention.
Embodiment
Referring to attached drawing, the present invention will be described in detail.
Carrier rocket development departments propose more stringent anti-mistake to ensure the success of launch mission, to micro-nano satellite structure
Carry and require, add the cost of design of satellite construction, development and verification experimental verification.Therefore, it is the power of improvement micro-nano satellite transmitter section
Environment is learned, reduces satellite development cost, a kind of efficient method is that increase is passively or actively isolation mounting on Payload Attach Fitting
To reduce the oscillating load for acting on satellite.
As shown in Figure 1,2,3, 4, a kind of satellite and the rocket adaptive device for micro-nano satellite vibration damping, including：Star end adaptation frame 1,
Cushion blocking center limited post 2, upper end cushion blocking 3, stop collar flange 4 on the outside of cushion blocking, lower end shake pad 5, arrow end adaptation frame 6, lock
Tight screw 7.The arrow end adaptation frame 6 of vibration damping adapter is rigidly connected with delivery Process of Piggyback Satellite stent, is suitable for satellite and the rocket interface；Fit at star end
Rigidly it is connected with frame 1 and micro-nano satellite installation interface, is suitable for satellite mounting surface interface；
Star end is adapted to frame 1 and is consolidated with the rigidity of stop collar flange on the outside of circumferentially distributed cushion blocking 4, and passes through upper end cushion blocking
3rd, lower end cushion blocking 5 is connected with arrow end adaptation frame 6, and upper end cushion blocking 3, lower end cushion blocking 5 are embedded in stop collar flange 4,
Center is then constrained by cushion blocking center limited post 2, and using lock-screw 7 it is adapted to arrow end frame 6 lock it is connected；
The quantity of stop collar flange 4 can be accepted or rejected according to bearing capacity demand on the outside of cushion blocking, and Fig. 1 and Fig. 3 sets forth this
Invent the schemes of 12 points of carryings and 8 points of carryings, the former can carry 30kg~50kg grades of micro-nano satellites, the latter can carry 1kg~
30kg grades of micro-nano satellites；When satellite is launched with carrier rocket or during Ground Vibration Test, star end adaptation frame 1 is with respect to arrow end adaptation frame
6 six-freedom degree generation vibration displacement, the unlubricated friction caused by the plastic deformation of upper end cushion blocking 3 and lower end cushion blocking 5
Wipe damping characteristic so that vibrational energy largely dissipates, and achievees the purpose that whole star vibration damping.
As shown in Figure 2 and Figure 4, the upper end cushion blocking 3 of vibration damping adapter and lower end cushion blocking 5 employ new metal
Elastomeric material, and hollow cylinder configuration is used, its inside cylindrical face cylinder 2 spacing with center completely attaches to, and outside cylinder is then
Completely attached to 4 medial surface of stop collar flange on the outside of cushion blocking, radial constraint is constituted above, for satellite oscillation crosswise or punching
Hit buffering vibration isolation；The anchor ring up and down of upper cushion blocking 3 is embedded in respectively in 2 head round recessed of center limited post and stop collar flange
On 4 in round recessed, the anchor ring up and down of lower cushion blocking 5 is embedded in respectively in 4 times round recesseds of stop collar flange and arrow end adaptation frame 6
In the groove of upper surface, axial constraint is together constituted after being fastened above by lock-screw 7, for satellite extensional vibration or punching
Hit buffering vibration isolation；
The vibration in three rotational freedom directions of satellite is then adapted to frame 1 and the one of cushion blocking stop collar flange 4 by star end
Change thaumatropy axially or radially to vibrate for cushion blocking, so as to can reach the vibration or damping of shocks vibration isolation in rotational freedom direction
Purpose.
As shown in figure 5, it is the signal of the rigidity preferred flow of upper end cushion blocking 3 and lower end cushion blocking 5, as subtracting in the present invention
The key link for design of shaking.After delivery ICD interfaces and design of satellites scheme determine, according to satellite gross mass and delivery to defending
The mechanics interface condition of star, including rigidity, Static Design load, low frequency sinusoidal vibration condition, high frequency random vibration condition and punching
The requirement for bearing capacity that condition etc. is converted to cushion blocking is hit, dynamic load therein is typically chosen static(al) equivalence principle, simultaneous selection
Largest enveloping load simultaneously leaves defined design margin, and selecting the cushion blocking of proper stiffness, (including range in stiffness and carrying subtract
Shake quantity of pad etc.)；
Necessary experimental test is carried out for the rigidity of primary election cushion blocking, using test data in combination with whole star finite element
Model is combined the analysis of body coupling Simulation, is determined to participate in the rigidity of the cushion blocking of next step experiment sieving according to analysis result,
Generally increase the cushion blocking of corresponding rigidity in the positive and negative scope of proper stiffness value for analyzing selection, testpieces, final complete as a comparison
Take turns and screen into cushion blocking second, determine the rigidity of cushion blocking testpieces；
Optimal Stiffness cushion blocking is selected using cushion blocking rigidity screening test：Rejected not using feature level scan test
Meet the cushion blocking of whole star rigidity requirement, cannot meet satellite dynamic load using impact, sinusoidal vibration and random vibration rejecting
It is required that cushion blocking, and further determine that the highest cushion blocking rigidity of damping efficiency is preferred result.
Upper end cushion blocking (3) and lower end cushion blocking (5) selection meet the specific side of the cushion blocking of satellite dynamic load requirement
Method is：
(1) delivery ICD interfaces and design of satellites scheme are determined；
(2) the mechanics interface condition according to satellite gross mass with delivery to satellite, including whole star rigidity condition, Static Design
Load, low frequency sinusoidal vibration condition, high frequency random vibration condition and impact condition, are converted to the requirement for bearing capacity of cushion blocking, just
The cushion blocking of proper stiffness scope and quantity is selected, calculation formula is as follows：
In formula,The respectively minimum rigidity value of cushion blocking vertical and horizontal, primary election cushion blocking rigidity should not
Less than the minimum rigidity value；WithRespectively cushion blocking vertical and horizontal allow maximum displacement；M and HcRespectively satellite
Quality and height of center of mass；Amax=max { rAsin,3Arand, AsinFor satellite sinusoidal vibration condition peak accelerator,For satellite random vibration condition peak accelerator, P (f) is random vibration test condition power spectrum
Spend function；Dynamics amplification coefficient when r is satellite sinusoidal vibration at barycenter with respect to satellite and the rocket interface；R is damper distribution circle half
Footpath；N is damper distributed quantity；θiFor i-th of damper position angle, damper installation center point is defined as with being distributed in circle
The line of heart point, the angle between the line and direction of vibration axis；I numbers for damper, on definition vibration direction of principal axis in distance
The farthest damper numbering of heart point is 1.In above-mentioned parameter, generally takeWithFor 2.5mm, r values are 5, f0Experience value
200Hz~300Hz.
(3) experimental test is carried out for the rigidity of primary election cushion blocking, its BUSH is created according to the test value of cushion blocking rigidity
Finite element unit, is combined the analysis of body coupling Simulation with reference to whole star finite element model, obtains satellite fundamental frequency ωa, according to following
Formula determines the cushion blocking rigidity for meeting condition, participates in next step experiment sieving：
ωa≥κωmin
In formula, ωminLower limit is required for whole star rigidity condition, κ is safety coefficient, general value 1.5.
(4) mechanical structure of satellite is combined, and is rejected using feature level scan test and does not meet subtracting for whole star rigidity requirement
Shake pad, i.e. experiment obtains satellite fundamental frequency ωtMeet ωt≥ωmin；Further, impact, sinusoidal vibration and random vibration test are utilized
Data verification cushion blocking bearing capacity and the damping efficiency for determining each state cushion blocking, i.e.,：
In formula,WithRespectively expire magnitude vibration experiment before and after test and measure satellite fundamental frequency, ηiFor i-th of damper
The damping efficiency of test specimen, L are damper testpieces number,WithRespectively satellite is with vibration damping i and without vibration damping i
Dynamic response peak accelerator value (including the total root-mean-square value of random vibration acceleration responsive).According to above-mentioned formula, pick
Except that cannot meet cushion blocking satellite rigidity and dynamic load delivery request or that damping efficiency is relatively low, maximum η is takeniCushion blocking
Rigidity is preferred result.
Step 3 increases the cushion blocking of corresponding rigidity in the positive and negative scope of proper stiffness value for analyzing selection, tests as a comparison
Part, cushion blocking testpieces rigidity upper limit value are calculated according to equation below：
In formula,The respectively maximum rigidity value upper limit of cushion blocking vertical and horizontal, primary election cushion blocking rigidity
Should without departing from the upper limit value,WithRespectively cushion blocking vertical and horizontal allow least displacement, usual value 2mm.Vibration damping
Pad testpieces rigidity lower limit can less thanWithSelected within the 10% of calculated value, finally complete to subtract according to step 4
The pad second that shakes wheel screening, determines the optimal rigidity of cushion blocking testpieces.
The present invention by the satellite and the rocket mechanical interface adaptation and satellite system irrespective of size vibration damping carry out integrated design, suitable for 1kg~
The satellite and the rocket adaptive device of 50kg grades of micro-nano satellite vibration dampings, you can meet the micro-nano satellite unlocking mechanism and rocket body stent of annulus configuration
Connection adaptation, but also with good damping property and shock resistance, to be effectively improved the mechanical ring of micro-nano satellite transmitter section
Border；Meanwhile the present invention has formulated the complete simulation analysis of set of system and verification for the preferred of its up/down cushion blocking proper stiffness
Experiment process, for the preferred of cushion blocking rigidity, to adapt to the requirement of the particular surroundings of AEROSPACE APPLICATION.
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (9)
1. a kind of satellite and the rocket adaptive device for micro-nano satellite vibration damping, it is characterised in that including star end adaptation frame (1), cushion blocking
Center limited post (2), upper end cushion blocking (3), stop collar flange (4), lower end cushion blocking (5) and arrow end adaptation frame on the outside of cushion blocking
(6), star end adaptation frame (1) is rigidly consolidated with stop collar flange (4) on the outside of circumferentially distributed cushion blocking, and passes through upper end cushion blocking
(3), lower end cushion blocking (5) is connected with arrow end adaptation frame (6), and upper end cushion blocking (3), lower end cushion blocking (5) are embedded in vibration damping
In pad outside stop collar flange (4), constrained centrally through cushion blocking center limited post (2)；
Upper end cushion blocking (3) and lower end cushion blocking (5) selection meet the cushion blocking of satellite dynamic load requirement；
Arrow end adaptation frame (6) is rigidly connected with delivery Process of Piggyback Satellite stent, is suitable for satellite and the rocket interface；Star end adaptation frame (1) and micro-nano
Satellite installation interface is rigidly connected, and is suitable for satellite mounting surface interface.
2. a kind of satellite and the rocket adaptive device for micro-nano satellite vibration damping as claimed in claim 1, it is characterised in that outside cushion blocking
The quantity of side stop collar flange (4) accepts or rejects preferably 12 points carryings and 8 points of carryings according to bearing capacity demand.
A kind of 3. satellite and the rocket adaptive device for micro-nano satellite vibration damping as claimed in claim 1, it is characterised in that upper end vibration damping
Pad (3) and lower end cushion blocking (5) use metal rubber material, are hollow cylinder configuration.
A kind of 4. satellite and the rocket adaptive device for micro-nano satellite vibration damping as claimed in claim 3, it is characterised in that upper end vibration damping
Pad (3) and the inside cylindrical face of lower end cushion blocking (5) to completely attach to the face of cushion blocking center limited post (2), outside cylinder is then
Completely attached to stop collar flange (4) medial surface on the outside of cushion blocking, form radial constraint, to realize to satellite oscillation crosswise or punching
Hit buffering vibration isolation.
A kind of 5. satellite and the rocket adaptive device for micro-nano satellite vibration damping as claimed in claim 1, it is characterised in that upper cushion blocking
(3) anchor ring up and down is embedded in respectively in the round recessed of cushion blocking center limited post (2) head and stop collar method on the outside of cushion blocking
On blue (4) in round recessed, the anchor ring up and down of lower cushion blocking (5) is embedded on the outside of cushion blocking circle under stop collar flange (4) respectively
In the groove of in groove and arrow end adaptation frame (6) upper surface.
A kind of 6. satellite and the rocket adaptive device for micro-nano satellite vibration damping as claimed in claim 1, it is characterised in that three, satellite
The vibration in rotational freedom direction is adapted to frame (1) and cushion blocking stop collar flange (4) integral structure and is converted into by star end to be subtracted
The pad that shakes axially or radially vibrates.
A kind of 7. satellite and the rocket adaptive device for micro-nano satellite vibration damping as claimed in claim 1, it is characterised in that upper end vibration damping
Pad (3) and lower end cushion blocking (5) select meet satellite dynamic load requirement cushion blocking method for：
(1) delivery ICD interfaces and design of satellites scheme are determined；
(2) the mechanics interface condition according to satellite gross mass with delivery to satellite, including whole star rigidity condition, Static Design carry
Lotus, low frequency sinusoidal vibration condition, high frequency random vibration condition and impact condition, are converted to the requirement for bearing capacity of cushion blocking, primary election
Go out the cushion blocking of proper stiffness scope and quantity, calculation formula is as follows：
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</mrow>
<mrow>
<msubsup>
<mi>ND</mi>
<mi>max</mi>
<mi>v</mi>
</msubsup>
</mrow>
</mfrac>
<mo>}</mo>
</mrow>
</mtd>
</mtr>
<mtr>
<mtd>
<mrow>
<msubsup>
<mi>K</mi>
<mi>min</mi>
<mi>v</mi>
</msubsup>
<mo>=</mo>
<mfrac>
<mrow>
<msub>
<mi>MA</mi>
<mi>max</mi>
</msub>
</mrow>
<mrow>
<msubsup>
<mi>ND</mi>
<mi>max</mi>
<mi>h</mi>
</msubsup>
</mrow>
</mfrac>
</mrow>
</mtd>
</mtr>
</mtable>
</mfenced>
In formula,The respectively minimum rigidity value of cushion blocking vertical and horizontal, primary election cushion blocking rigidity should be not less than should
Minimum rigidity value；WithRespectively cushion blocking vertical and horizontal allow maximum displacement；M and HcRespectively satellite quality and
Height of center of mass；Amax=max { rAsin,3Arand, AsinFor satellite sinusoidal vibration condition peak accelerator,For satellite random vibration condition peak accelerator, P (f) is random vibration test condition power spectrum
Spend function；Dynamics amplification coefficient when r is satellite sinusoidal vibration at barycenter with respect to satellite and the rocket interface；R is damper distribution circle half
Footpath；N is damper distributed quantity；θiFor i-th of damper position angle, damper installation center point is defined as with being distributed in circle
The line of heart point, the angle between the line and direction of vibration axis；I numbers for damper, on definition vibration direction of principal axis in distance
The farthest damper numbering of heart point is 1；
(3) experimental test is carried out for the rigidity of primary election cushion blocking, it is limited that its BUSH is created according to the test value of cushion blocking rigidity
First unit, is combined the analysis of body coupling Simulation with reference to whole star finite element model, obtains satellite fundamental frequency ωa, according to the following formula
Determine the cushion blocking rigidity for meeting condition, participate in next step experiment sieving：
ωa≥κωmin
In formula, ωminLower limit is required for whole star rigidity condition, κ is safety coefficient；
(4) mechanical structure of satellite is combined, and the cushion blocking for not meeting whole star rigidity requirement is rejected using feature level scan test,
I.e. experiment obtains satellite fundamental frequency ωtMeet ωt≥ωmin；Further, impact, sinusoidal vibration and random vibration test data are utilized
Verify cushion blocking bearing capacity and determine the damping efficiency of each state cushion blocking, i.e.,：
<mrow>
<mrow>
<mo>|</mo>
<mrow>
<mn>1</mn>
<mo>-</mo>
<msubsup>
<mi>&omega;</mi>
<mi>t</mi>
<mrow>
<mi>e</mi>
<mi>n</mi>
<mi>d</mi>
</mrow>
</msubsup>
<mo>/</mo>
<msubsup>
<mi>&omega;</mi>
<mi>t</mi>
<mrow>
<mi>i</mi>
<mi>n</mi>
<mi>i</mi>
</mrow>
</msubsup>
</mrow>
<mo>|</mo>
</mrow>
<mo>&le;</mo>
<mn>5</mn>
<mi>%</mi>
</mrow>
<mrow>
<msub>
<mi>&eta;</mi>
<mi>i</mi>
</msub>
<mo>=</mo>
<mrow>
<mo>(</mo>
<mn>1</mn>
<mo>-</mo>
<msubsup>
<mi>A</mi>
<mi>i</mi>
<mrow>
<mi>d</mi>
<mi>a</mi>
<mi>m</mi>
<mi>p</mi>
<mi>e</mi>
<mi>d</mi>
</mrow>
</msubsup>
<mo>/</mo>
<msubsup>
<mi>A</mi>
<mi>i</mi>
<mrow>
<mi>u</mi>
<mi>n</mi>
<mi>d</mi>
<mi>a</mi>
<mi>m</mi>
<mi>p</mi>
<mi>e</mi>
<mi>d</mi>
</mrow>
</msubsup>
<mo>)</mo>
</mrow>
<mo>&times;</mo>
<mn>100</mn>
<mi>%</mi>
<mo>,</mo>
<mi>i</mi>
<mo>=</mo>
<mn>1</mn>
<mo>,</mo>
<mn>2</mn>
<mo>,</mo>
<mn>...</mn>
<mo>,</mo>
<mi>L</mi>
</mrow>
In formula,WithRespectively expire magnitude vibration experiment before and after test and measure satellite fundamental frequency, ηiFor i-th of damper test specimen
Damping efficiency, L is damper testpieces number,WithRespectively satellite is with vibration damping i and without the dynamic of vibration damping i
The peak accelerator value of mechanical response, according to above-mentioned formula, satellite rigidity and dynamic load delivery request cannot be met by rejecting
Or the cushion blocking that damping efficiency is relatively low, take maximum ηiCushion blocking rigidity be preferred result.
8. a kind of satellite and the rocket adaptive device for micro-nano satellite vibration damping as claimed in claim 7, it is characterised in that step 3 exists
Analyzing the positive and negative scope of proper stiffness value of selection increases the cushion blocking of corresponding rigidity, as a comparison testpieces, cushion blocking testpieces
Rigidity upper limit value is calculated according to equation below：
<mfenced open = "{" close = "">
<mtable>
<mtr>
<mtd>
<mrow>
<msubsup>
<mi>K</mi>
<mi>max</mi>
<mi>h</mi>
</msubsup>
<mo>=</mo>
<mi>min</mi>
<mo>{</mo>
<mfrac>
<mrow>
<msub>
<mi>H</mi>
<mi>c</mi>
</msub>
<msub>
<mi>MA</mi>
<mi>max</mi>
</msub>
<msub>
<mi>cos&theta;</mi>
<mn>1</mn>
</msub>
</mrow>
<mrow>
<mn>4</mn>
<msubsup>
<mi>D</mi>
<mi>min</mi>
<mi>v</mi>
</msubsup>
<mi>R</mi>
<msubsup>
<mo>&Sigma;</mo>
<mrow>
<mi>i</mi>
<mo>=</mo>
<mn>1</mn>
</mrow>
<mi>N</mi>
</msubsup>
<msup>
<mi>cos</mi>
<mn>2</mn>
</msup>
<msub>
<mi>&theta;</mi>
<mi>i</mi>
</msub>
</mrow>
</mfrac>
<mo>,</mo>
<mfrac>
<mrow>
<msub>
<mi>MA</mi>
<mi>max</mi>
</msub>
</mrow>
<mrow>
<msubsup>
<mi>ND</mi>
<mi>min</mi>
<mi>v</mi>
</msubsup>
</mrow>
</mfrac>
<mo>}</mo>
</mrow>
</mtd>
</mtr>
<mtr>
<mtd>
<mrow>
<msubsup>
<mi>K</mi>
<mi>max</mi>
<mi>v</mi>
</msubsup>
<mo>=</mo>
<mfrac>
<mrow>
<msub>
<mi>MA</mi>
<mi>max</mi>
</msub>
</mrow>
<mrow>
<msubsup>
<mi>ND</mi>
<mi>min</mi>
<mi>h</mi>
</msubsup>
</mrow>
</mfrac>
</mrow>
</mtd>
</mtr>
</mtable>
</mfenced>
In formula,Respectively the maximum rigidity value upper limit of cushion blocking vertical and horizontal, primary election cushion blocking rigidity should not surpass
Go out the upper limit value,WithRespectively cushion blocking vertical and horizontal allow least displacement, cushion blocking testpieces rigidity lower limit
Can less thanWithSelected within the 10% of calculated value, finally complete the wheel screening of cushion blocking second according to step 4, really
Determine the optimal rigidity of cushion blocking testpieces.
A kind of 9. satellite and the rocket adaptive device for micro-nano satellite vibration damping as claimed in claim 7, it is characterised in that in step 2,
TakeWithFor 2.5mm, r values are 5, f0Experience value is 200Hz~300Hz.
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| CN109068530A (en) * | 2018-07-11 | 2018-12-21 | 上海微小卫星工程中心 | A kind of high heat consumption single machine of the satellite that vibration damping is thermally conductive |
| CN110486583A (en) * | 2019-07-31 | 2019-11-22 | 中国航发沈阳发动机研究所 | A kind of sensor vibration damping spacing support construction |
| CN110816893A (en) * | 2019-10-16 | 2020-02-21 | 上海空间电源研究所 | Limiting device for dismounting large-space bearing product |
| CN111619831A (en) * | 2020-04-29 | 2020-09-04 | 航天东方红卫星有限公司 | Connecting rod type satellite-rocket separation mechanism |
| CN112032245A (en) * | 2020-09-11 | 2020-12-04 | 上海航天控制技术研究所 | Vibration reduction system for satellite-borne accelerometer combination |
| CN112182778A (en) * | 2020-10-27 | 2021-01-05 | 中国运载火箭技术研究院 | Vibration analysis method, device, terminal and medium for carrier rocket equipment support |
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| CN109068530A (en) * | 2018-07-11 | 2018-12-21 | 上海微小卫星工程中心 | A kind of high heat consumption single machine of the satellite that vibration damping is thermally conductive |
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| CN110816893A (en) * | 2019-10-16 | 2020-02-21 | 上海空间电源研究所 | Limiting device for dismounting large-space bearing product |
| CN110816893B (en) * | 2019-10-16 | 2021-02-09 | 上海空间电源研究所 | Limiting device for dismounting large-space bearing product |
| CN111619831A (en) * | 2020-04-29 | 2020-09-04 | 航天东方红卫星有限公司 | Connecting rod type satellite-rocket separation mechanism |
| CN112032245A (en) * | 2020-09-11 | 2020-12-04 | 上海航天控制技术研究所 | Vibration reduction system for satellite-borne accelerometer combination |
| CN112182778A (en) * | 2020-10-27 | 2021-01-05 | 中国运载火箭技术研究院 | Vibration analysis method, device, terminal and medium for carrier rocket equipment support |
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