RU98109554A - TEST METHODS OF STAFF SPACE VEHICLES - Google Patents
TEST METHODS OF STAFF SPACE VEHICLESInfo
- Publication number
- RU98109554A RU98109554A RU98109554/28A RU98109554A RU98109554A RU 98109554 A RU98109554 A RU 98109554A RU 98109554/28 A RU98109554/28 A RU 98109554/28A RU 98109554 A RU98109554 A RU 98109554A RU 98109554 A RU98109554 A RU 98109554A
- Authority
- RU
- Russia
- Prior art keywords
- test mode
- transmission
- frequency
- coefficient
- shock
- Prior art date
Links
- 238000010998 test method Methods 0.000 title claims 2
- 230000005540 biological transmission Effects 0.000 claims 10
- 238000001228 spectrum Methods 0.000 claims 9
- 230000035939 shock Effects 0.000 claims 5
- 230000001133 acceleration Effects 0.000 claims 3
- 230000003595 spectral Effects 0.000 claims 3
- 230000000694 effects Effects 0.000 claims 1
- 230000035945 sensitivity Effects 0.000 claims 1
Claims (1)
G(ω,g) = Arg minΦ,
где
где M - количество точек контроля;
j = 1 - коэффициент, связанный с амплитудным спектром;
j = 2 - коэффициент, связанный с широкополосной случайной вибрацией;
j = 3 - коэффициент, связанный с ударным спектром ускорений;
N - количество частотных поддиапазонов;
ζij - весовой коэффициент для амплитудных спектров;
|KA| - модуль максимального значения коэффициента передачи по амплитудному спектру;
Kij Sm - коэффициент передачи, связанный со спектральной плотностью мощности виброускорений в "m" точке при j воздействии в "i" частотном поддиапазоне;
ηij - весовой коэффициент для спектральной плотности мощности;
|KS| - модуль максимального значения коэффициента передачи по спектральной плотности мощности;
Kij Vm - коэффициент передачи, связанный с ударными спектрами в "m" точке при j воздействии в "i" частотном поддиапазоне;
θij - весовой коэффициент для ударных спектров;
|KV| - модуль максимального значения коэффициента передачи по ударному спектру,
после чего нагружению подвергают штатное изделие сначала на минимально возможных уровнях от испытательного режима, а затем на откорректированном по приведенной выше формуле с учетом коэффициентов передачи штатного изделия испытательном режиме.A test method for full-time spacecraft, which consists of setting the frequency test mode, obtaining transmission coefficients and then adjusting the test mode, characterized in that when testing on a dynamically similar layout, the transmission coefficients are determined sequentially under loading using the oscillating frequency method, the method of broadband random vibration, the method shock acceleration spectra, while the effects vary in amplitude discretely from the minimum, determined by the sensitivity defining and recording equipment to the levels obtained with the full-scale operation, a test mode is formed by the condition not exceeding admissible values of the control points in each frequency podiapazone by the formula:
G (ω, g) = Arg minΦ,
Where
where M is the number of control points;
j = 1 is the coefficient associated with the amplitude spectrum;
j = 2 is the coefficient associated with broadband random vibration;
j = 3 is the coefficient associated with the shock spectrum of accelerations;
N is the number of frequency subbands;
ζ ij is the weight coefficient for the amplitude spectra;
| K A | - the module of the maximum value of the transmission coefficient in the amplitude spectrum;
K ij Sm is the transmission coefficient associated with the power spectral density of vibration acceleration at the "m" point with j exposure in the "i" frequency sub-band;
η ij is the weight coefficient for the power spectral density;
| K S | - the modulus of the maximum value of the transmission coefficient by power spectral density;
K ij Vm is the transmission coefficient associated with the shock spectra at the "m" point under j exposure in the "i" frequency sub-band;
θ ij is the weight coefficient for the shock spectra;
| K V | - the module of the maximum value of the transmission coefficient in the shock spectrum,
then the standard product is subjected to loading first at the lowest possible levels from the test mode, and then on the test mode corrected according to the above formula, taking into account the transmission coefficients of the standard product.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU98109554A RU2171974C2 (en) | 1998-05-18 | 1998-05-18 | Spacecraft testing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU98109554A RU2171974C2 (en) | 1998-05-18 | 1998-05-18 | Spacecraft testing method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| RU98109554A true RU98109554A (en) | 2000-02-20 |
| RU2171974C2 RU2171974C2 (en) | 2001-08-10 |
Family
ID=48231272
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU98109554A RU2171974C2 (en) | 1998-05-18 | 1998-05-18 | Spacecraft testing method |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2171974C2 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2756143C1 (en) * | 2020-11-17 | 2021-09-28 | Акционерное общество "Центральный научно-исследовательский институт машиностроения" (АО "ЦНИИмаш") | Method for testing space technology products for vibroacoustic impact |
-
1998
- 1998-05-18 RU RU98109554A patent/RU2171974C2/en not_active IP Right Cessation
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