ISO 23569:2021

INTERNATIONAL ISO
STANDARD 23569
First edition
2021-11
Space systems — Spacecraft
system level radio frequency (RF)
performance test in compact range
Systèmes spatiaux — Essai de performance des radiofréquences (RF)
dans une gamme compacte au niveau du système de l'engin spatial
Reference number
© ISO 2021
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ii
Contents Page
Foreword .iv
Introduction .v
1 Scope . 1
2 Normative references . 1
3 Terms and definitions . 1
4 Abbreviated terms . 1
5 Test facility . .2
6 Test requirement . 4
6.1 System level RF performance test . 4
6.2 RF performance test in compact range . 5
7 Test item . 6
8 RF performance test methods .7
8.1 EIRP test . 7
8.1.1 Test purpose . 7
8.1.2 Test principle . 7
8.1.3 Illustrative test procedure . 7
8.2 G/T-test . 8
8.2.1 Test purpose . 8
8.2.2 Test principle . 8
8.2.3 Illustrative test procedure . 9
8.3 SPFD test . 9
8.3.1 Test purpose . 9
8.3.2 Test principle . 9
8.3.3 Illustrative test procedure . 10
8.4 AFR test . 10
8.4.1 Test purpose . 10
8.4.2 Test principle . 10
8.4.3 Illustrative test procedure . 10
8.5 Group delay test . 10
8.5.1 Test purpose . 10
8.5.2 Test principle . 10
8.5.3 Illustrative test procedure . 11
8.6 PIM test. 11
8.6.1 Test purpose . 11
8.6.2 Test principle . 11
8.6.3 Illustrative test procedure . 11
9 Test report .11
Annex A (informative) Illustrative procedures for EIRP test.12
Annex B (informative) Illustrative procedures for G/T-test .16
Annex C (informative) Illustrative procedures for SPFD test .23
Annex D (informative) Illustrative procedures for AFR test .27
Annex E (informative) Illustrative procedures for group delay test .32
Annex F (informative) Illustrative procedures for PIM test .34
Annex G (informative) Derivation for G/T formula .38
Bibliography . 44
iii
Foreword
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iv
Introduction
System level test for RF performance of spacecraft, which is the test for spacecraft expected
performance on orbit, includes test of EIRP, G/T, SPFD, AFR, group delay, PIM, etc. In some conditions, it
also includes verification of the antenna pattern on two crossed planes (normally the antenna pattern
is measured in unit level and subsystem level; if it is necessary to measure in system level, the antenna
pattern on two crossed planes would be chosen for verification purpose). Compact range is suitable for
spacecraft full-link RF performance test, which includes uplink and downlink.
Currently there are well-defined requirements for acceptance test of integrated spacecraft as final RF
performance verification tests, especially for commercial communication spacecraft. RF performance
test for the payload system (including the transponder and Tx/Rx antennas) is becoming more and more
important and should be verified before launch. At present, the system level RF performance test has
become one important step listed in the spacecraft production flow. It is carried out to verify whether
there is unexpected variation during the assembling of the spacecraft and whether the RF performance
in coverage area (footprint) can satisfy the specification.
According to ISO 15864, the system level RF performance test items have been identified as necessary
functional performance parameters in acceptance tests, so they can be tailored to the test requirement
for each kind of spacecraft or test plan.
v
INTERNATIONAL STANDARD ISO 23569:2021(E)
Space systems — Spacecraft system level radio frequency
(RF) performance test in compact range
1 Scope
This document specifies the verification test activities for assessing the RF performance of integrated
spacecraft, including test items, test requirements, and typical test procedures, test facility and
chamber environment, with respect to the testing using compact range. This document is applicable to
the RF performance test for spacecraft at system level using compact range.
2 Normative references
There are no normative references in this document.
3 Terms and definitions
For the purposes of this document, the following terms and definitions apply.
ISO and IEC maintain terminology databases for use in standardization at the following addresses:
— ISO Online browsing platform: available at https:// www .iso .org/ obp
— IEC Electropedia: available at https:// www .electropedia .org/
3.1
nominal plane wave axis of compact range
NPA
axis of propagation of a single plane wave generated by the compact range reflector
3.2
effective free space distance in compact range
R
equivalent distance from the feed, where spherical attenuation exists
4 Abbreviated terms
AFR amplitude-frequency response
AM amplitude modulation
ALC automatic level control
CR compact range
DUT device under test
EIRP effective isotropically radiated power
EM electrical model
FM frequency modulation
G/T ratio of gain-to-noise temperature (quality factor of spacecraft receiving system)
PIM passive intermodulation
QZ quiet zone
RBW resolution bandwidth
RF radio frequency
Rx receive
SERAP serration radiation protection structure
SPFD saturated power flux density
Tx transmit
CW continuous wave
5 Test facility
According to Reference [1], the compact range is one in which the test antenna is illuminated by the
collimated energy in the aperture of a larger point or line focus antenna. For example, a precision
paraboloidal antenna can be used to collimate the energy, as shown schematically in Figure 1, it is more
suitable for test antenna; a precision dual reflector antenna can be used to collimate the energy also,
like Cassegrain dual reflector antenna which is more suitable for the spacecraft system level test, as
shown schematically in Figure 2.
Key
1 quiet zone (QZ)
2 test antenna
3 range Tx/Rx feed
4 focal point
Figure 1 — Schematic representation of a compact range using a reflector and feed
Key
1 quiet zone (QZ)
2 spacecraft
3 Tx/Rx antenna
4 Tx/Rx antenna
5 range Tx/Rx feed
6 focal point
7 main reflection
8 subreflector
Figure 2 — Schematic representation of a compact range using a dual reflector and feed
The test facility is mainly composed of a range illuminating subsystem, a positioner subsystem, an
anechoic chamber and RF test instruments.
The range illuminating subsystem, which includes the range reflector and the range feeds, shall be
able to provide the plane wave with flatter amplitude and phase distribution in the QZ. The alignment
between the range reflector and the range feed can be done annually or biennially; the nominal plane
wave axis of compact range (NPA) direction can be shown (by cubic mirror or others). The reflector
shall have sufficient accuracy.
The positioner subsystem, which includes the DUT positioner and the range feed positioners, shall be
able to rotate the DUT and range feeds with sufficient accuracy. Due to the heft of the DUT, the DUT
positioner can be equipped with counter weight for balance.
The anechoic chamber, which is covered with several types of absorbing material, can provide test
environment with low reflectivity.
As part of the test facility, related RF instruments shall be provided, to produce uplink RF signal and
to measure downlink RF radiating signal of the DUT, the standard RF instruments are listed in Table 1.
The frequency range, linearity and dynamic range of the RF measurement system shall satisfy the test
requirements. Part of the measurement equipment that makes up the test facility can be calibrated
periodically or in advance of the test by a national metrology institute.
Table 1 — Standard RF instruments
No. Name of instrument Function Applicated test item
EIRP, G/T, SPFD, AFR,
group delay.
1 Source Produce uplink transmitting signal.
Two sources are needed for PIM
test item.
Monitor the downlink receiving signal and
spectrum;
2 Spectrum analyser EIRP, G/T, SPFD, AFR, PIM
Measure the power of downlink receiving
signal.
Measure the power of downlink receiving
3 Power meter EIRP, SPFD
signal.
Reduce the power of downlink signal or
4 Fixed attenuator EIRP, G/T, SPFD, AFR, PIM
Reduce the power of uplink signal.
5 Coupler Couple a part of power from path. EIRP
Combine the signals of two paths with differ-
6 Power hybrid PIM
ent frequencies into one path.
Produce the AM or FM modulation signal
AM or FM modulation
7 which will be carried by uplink and downlink Group delay
signal generator
signal.
Convert the downlink signal to lower frequen-
8 Down converter Group delay
cy.
Demodulate the downlink signal to get the AM
9 Modem Group delay
or FM modulation signal.
Compare the two AM or FM modulation sig-
Modulation domain nal, one is carried by uplink signal, another is
10 Group delay
analyser carried by downlink signal, to get the related
time delay.
Data acquisition com- Run automatically controlled by computer
11 AFR
puter software to complete the data acquisition.
6 Test requirement
6.1 System level RF performance test
When the spacecraft system is very complex, system level RF performance test should be planned based
on the specifications and listed in the spacecraft production flow. The following preparations should be
considered:
a) DUT test scheme, such as which channel and how many channels will be tested;
b) goal budget of EIRP, G/T, SPFD for spacecraft system;
c) installation of the DUT self-alignment target which will be in accordance with the NPA;
d) installation of wind pipes for spacecraft heat dissipation, if necessary;
e) installation of additional humidifier/dehumidifier for special sensitive payload, if necessary;
f) provision of a suitable adapter as interface between spacecraft and the DUT positioner.
6.2 RF performance test in compact range
In order to verify whether the final RF performance can satisfy the specification, and to perform the RF
tests, the compact range system should fulfil the following conditions for either facility or customer's
equipment.
a) The QZ quality needs to consider the customer’s requirement.
b) The DUT positioner’s maximum bending moment shall be strong enough for spacecraft holding.
Based on the DUT’s weight and centre of gravity, the positioner’s counter weight can be calculated.
Both of the positioner’s elevation and azimuth axes should be balanced with counter weight, so as
to maintain the rotated angle accuracy.
c) The range reflection sources should be reduced. High-performance absorbing material should be
placed between the feed and the DUT to further reduce the effects of the diffraction from the feed
structure. It also helps to suppress any direct radiation from the feed antenna to the test region.
If the compact range has baffle or SERAP, position the baffle in the line-of-sight between the feed
and the QZ to reduce stray radiation directed to the QZ; and position the SERAP in an appropriate
place to prevent the feed from illuminating the main reflector serrations. The position of baffle or
SERAP in compact range is shown in Figure 3.
Key
1 quiet zone (QZ)
2 baffle
3 range Tx/Rx feed
4 focal point
5 SERAP
6 main reflector
7 subreflector
Figure 3 — Schematic of baffle and SERAP’s position
d) The spacecraft’s support structure shall be covered with absorbing material, so as to reduce
additional reflection as far as possible.
e) In the anechoic chamber, the range feed local area shall be covered with high power absorbing
material, because the spacecraft downlink is high power transmitting state, this area shall
withstand high power, if necessary. The temperature of this area shall be monitored during the
test.
Also, the range reflector local area shall be maintained in stable temperature state by running the
air-condition system continually if necessary, depending on manufacturer’s requirement, so as to
maintain stable QZ performance.
f) The capability of crane and hook need to consider the requirement of spacecraft lifting.
g) The electrical isolation / grounding should be available.
Normally, three grounding terminals isolated from each other can be prepared, and separately
connected to spacecraft surface, test instrument, and any other test equipment temporarily used in
the chamber.
h) The earth resistances need to consider the customer’s requirement.
i) Because of the high-power level in spacecraft system level test, the hazard areas should be
identified with warning plates and / or warning lamps at any personnel gate.
j) Calculate the RF link budget.
k) Do self-calibration for the RF equipment before each absolute value test if necessary, e.g. using a
power meter for absolute power test.
l) Do RF-cable loss calibration, if necessary.
m) Prepare the gain calibration data of the range feeds.
n) Prepare the antenna pattern data measured in subsystem level EM/RM (radiation mock-up).
7 Test item
RF performance test items described in this document refer to tests of EIRP, G/T, SPFD, AFR, group
delay and PIM.
RF performance test items are tailored to the test requirement for each kind of spacecraft or test plan.
The channels selected to be tested depend on the test requirement.
To verify the spacecraft’s uplink performance, G/T and SPFD shall be tested. The spacecraft body
together with the Rx antennas shall be located in the QZ, while the Tx range feed shall be located at the
focus of the range reflector.
To verify the spacecraft’s downlink performance, EIRP shall be tested. The spacecraft body together
with the Tx antennas shall be located in the QZ, while the Rx range feed shall be located at the focus of
the range reflector.
To verify the spacecraft’s full link performance, AFR and group delay shall be tested. For the AFR
test, the spacecraft body together with the Tx antennas or the spacecraft body together with the Rx
antennas shall be located in the QZ, while the Rx or the Tx range feed shall be located at the focus of the
range reflector, depending on whether output AFR or input AFR will be tested. For the group delay test,
the spacecraft body together with the Tx antennas and Rx antennas shall be located in the QZ, if the size
of the QZ is not enough to support the full link wireless test, this group delay test item will be tailored.
For a spacecraft antenna system which shares Rx/Tx signals, the PIM components of the spacecraft’s
downlink transmitting signal may go directly to the uplink channels. If PIM frequencies are within the
spacecraft’s uplink receiving frequency band, PIM shall be tested. The spacecraft body together with
the Tx antennas shall be located in the QZ, while the Rx range feed shall be located at the focus of the
range reflector.
The EIRP, SPFD and PIM test need to be done in saturation state, which means spacecraft’s uplink is
saturated. The saturation point can be determined by several methods, such as power/gain method, AM
number method, and by monitoring the telemetry parameters of spacecraft’s amplifier.
8 RF performance test methods
8.1 EIRP test
8.1.1 Test purpose
The purpose of the EIRP test is to measure and to evaluate EIRP values at the beam peak and/or at
a typical point in the spacecraft downlink coverage area (footprint), and to verify whether the EIRP
values can satisfy the goal budget and specifications. By combining the antenna pattern measured in
subsystem level EM/RM (radiation mock-up) and the system level measured EIRP values at the beam
peak and/or at a typical point, the EIRP coverage pattern can be obtained.
If necessary, a verification of the spacecraft’s Tx or Tx/Rx antenna radiation pattern can also be done on
two crossed planes in coverage area by using the downlink EIRP setup.
8.1.2 Test principle
In compact range, the spherical wave from the range feed is reflected by the reflector, as a plane wave,
to the QZ, wherein the spacecraft is located, then the equivalent spacecraft to earth RF link can be used
for system level RF performance test. The distance from the range feed to the reflector and then to the
QZ, is the effective free space distance in compact range, R; this value depends on the design of compact
range.
Based on the reciprocity of compact range, spacecraft’s downlink signal, Tx, is reflected by the range
reflector and goes back to the range feed, wherein R is the same. The EIRP can be obtained by measuring
the Rx signal received by the range feed. The EIRP can be calculated by Formulae (1), (2) and (3).
QG= ·P (1)
EIRP Tx,,satTxsat
PL·
Rx CR p,down
,
Q = (2)
EIRP
G
Rx,CR
 4πR 
L = (3)
p,down  
λ
 
down
where
L is the free space loss for the downlink signal;
p,down
R is the effective free space distance in compact range, m;
P is the received power measured at the output port of the range feed, W;
Rx,CR
G is the gain of Rx range feed.
Rx,CR
8.1.3 Illustrative test procedure
Two illustrative procedure examples for the EIRP test are provided in Annex A. The EIRP can be
measured by two methods: with full wireless link setup or with wireless downlink setup. The procedure
to be used depends on the test requirement and whether the size of QZ can satisfy the full link setup.
8.2 G/T-test
8.2.1 Test purpose
The purpose of the gain-to-noise temperature ratio, G/T, test is to measure and to evaluate G/T values
at the beam peak and/or at a typical point in the spacecraft’s uplink coverage area (footprint). The test
results show whether the G/T values can satisfy the goal budget and specifications. The G/T coverage
pattern can be obtained by combining the antenna pattern measured in subsystem level EM/RM
(radiation mock-up) and the system level measured G/T values at the beam peak and/or at a typical
point.
8.2.2 Test principle
As described in 8.1.2, the spacecraft is located in the QZ and illuminated by the plane wave. R is known
and depends on the design of the compact range.
The G/T can be measured in two different modes: the fixed gain mode and the automatic level control
(ALC) mode. The ALC mode requires one more step in the data acquisition compared with the fixed
gain mode. The major difference between these two modes is that the output power level varies with
the input power level in the fixed gain mode, whereas the output power level is constant in the ALC
mode.
a) G/T in the fixed gain mode is obtained from three sequential power level measurements:
1) noise power level, P , of the receiving test equipment, while the spacecraft transponder is
turning off, the RF output of range source is turning off also;
2) noise power level, P , of the receiving test equipment, including the spacecraft noise level, while
the spacecraft transponder is turning on, the RF output of range source is turning off;
3) power level, P , of the receiving test equipment, including the spacecraft noise level and carrier
power level, while the spacecraft transponder is turning on, the RF output of range source is
turning on also.
Then G/T can be calculated by Formulae (4), (5) and (6):
kB··LY··()−1 Y
p,up 21
r = (4)
GT/
QY·( −1)
EIRP,Tx,CR 1
YP=/P (5)
12 1
YP=/P (6)
23 2
where
k is the Boltzmann constant, J/K;
B is the noise bandwidth corresponding to the test bandwidth, Hz;
L is the free space loss for the uplink signal;
p,up
Q
is the EIRP of the Tx range feed, W.
EIRP,TxC, R
The detailed derivation for Formulae (4) and (7) can be found in Annex G.
b) The G/T in the ALC mode is obtained from four sequential power level measurements:
1) power level, P , of the receiving test equipment, including the spacecraft noise level and carrier
a
power, while the spacecraft transponder is turning on, the RF output of range source is turning
on also;
2) noise power level, P , of the receiving test equipment, including the spacecraft noise level (same
b
setup as, P , measurement), while the spacecraft transponder is turning on, the RF output of
a
range source is turning off;
3) power level, P , of the receiving test equipment, including the spacecraft noise level and carrier
c
power (same setup as P measurement, but EIRP at Tx range station is different);
a
4) noise power level, P , of the receiving test equipment, including the spacecraft noise level (same
d
setup as P measurement), while the spacecraft transponder is turning on, the RF output of
c
range source is turning off;
Then G/T can be calculated by Formula (7).
kB··L
 PP− PP− 
p,up
cd ab
r = · − (7)
 
GT/
PP− Q Q
db  EIRP,TxC,,R 21EIRP,TxC,,R 
where
k is the Boltzmann constant, J/K;
B is the noise bandwidth corresponding to the test bandwidth, Hz;
L is the free space loss for the uplink signal;
p,up
Q is the EIRP at Tx range station, when P and P are measured, W.
EIRP,TxC,,R 1 a b
The detailed derivation for G/T formulae can be found in Annex G.
8.2.3 Illustrative test procedure
Two illustrative procedure examples for the G/T-test are provided in Annex B. Both the G/T-test with
fixed gain mode and G/T-test with ALC mode can be measured by two methods: with full wireless link
setup or with wireless uplink setup. The procedure to be used depends on the test requirement and
whether the size of QZ can satisfy the full link setup.
8.3 SPFD test
8.3.1 Test purpose
The purpose of the saturated power flux density (SPFD) test is to measure and to evaluate SPFD values
at the beam peak and/or at a typical point in the spacecraft uplink coverage area. The test results show
whether the SPFD values can satisfy the goal budget and specifications.
If necessary, a verification of the spacecraft’s Rx antenna radiation pattern should be performed on two
crossed planes in coverage area with uplink SPFD setup.
8.3.2 Test principle
As described in 8.1.2, the spacecraft is located in the QZ, and illuminated by the plane wave. R is known
and depends on the design of compact range.
The SPFD presents the received power density value at the spacecraft Rx antenna in a certain direction.
Usually SPFD is measured with the output amplifier of the spacecraft in its saturated point. So SPFD
can be calculated by Formula (8):
 1 
BP= ··G (8)
SPFD Tx,,CR Tx CR  
 
4πR
where
P is the Tx power at Tx range feed, W;
Tx,CR
G is the gain of Tx range feed;
Tx,CR
R is the effective free space distance in compact range, m;
2 −2
1/4πR is identical to space distribution factor, m .
8.3.3 Illustrative test procedure
Two illustrative procedure examples for the SPFD test are provided in Annex C. The SPFD can be
measured by two methods: with full wireless link setup or with wireless downlink setup. The procedure
to be used depends on the test requirement and whether the size of the QZ can satisfy the full link setup.
8.4 AFR test
8.4.1 Test purpose
The purpose of amplitude-frequency response (AFR) test is to measure and to evaluate AFR curves
near the beam peak of the spacecraft uplink or downlink coverage area. The test results show whether
the AFR is flat enough to satisfy the specifications.
8.4.2 Test principle
As described in 8.1.2, the spacecraft is located in the QZ, and illuminated by the plane wave. R is known
and depends on the design of compact range.
Set the spacecraft’s uplink and downlink to make it operate in linear state, and change the frequency of
the range source with each specific step to get the amplitude-frequency performance curves.
8.4.3 Illustrative test procedure
Two illustrative procedure examples for ARF test are provided in Annex D. The ARF can be measured
by two methods: with full wireless link setup or with wireless uplink or downlink setup. The procedure
to be used depends on the test requirement and whether the size of the QZ can satisfy the full link setup.
8.5 Group delay test
8.5.1 Test purpose
The purpose of the group delay test is to measure and to evaluate group delay response curves near
the beam peak of the spacecraft uplink or downlink coverage area. The test results show whether the
group delay response curves can satisfy the specifications.
8.5.2 Test principle
As described in 8.1.2, the spacecraft is located in the QZ, and illuminated by the plane wave. R is known
and depends on the design of compact range.
Set the uplink and downlink of the spacecraft to make it operate in linear state, down convert and
de-modulate the downlink signal with modulation. The absolute delay in test frequency point can be
obtained by comparing the resulted signal with the original modulated signal. The group delay curve in
test band is obtained by changing the test frequency of the range source with each specific step.
8.5.3 Illustrative test procedure
The illustrative procedure example for the group delay test is provided in Annex E. The group delay test
only can be done in full link wireless setup, if the size of the QZ is not enough to support the full link
wireless test, this group delay test item will be tailored.
8.6 PIM test
8.6.1 Test purpose
The purpose of passive intermodulation (PIM) test is to measure and to evaluate PIM values at the
beam peak and/or typical point in the spacecraft uplink coverage area. The test results show whether
the PIM values can satisfy the PIM specifications.
8.6.2 Test principle
As described in 8.1.2, the spacecraft is located in the QZ, and illuminated by the plane wave.
As known, PIM can be represented as: f = ± m·f ± n·f , with two downlink signals, f and f ,
PIM 11 22 11 22
corresponding to two uplink carrier signals, f and f . For spacecraft antenna system which shares Rx/
1 2
Tx signals, if f falls in uplink frequency band, a relatively high level f interferes with the normal
PIM PIM
communication immediately.
To measure PIM in compact range is actually to measure the downlink signal harmonics, f , that
PIM,down
falls at spacecraft’s uplink operational band, f . This is different from the unit level PIM test. Only
PIM
f higher than the transponder’s noise spectrum can be detected. Usually the PIM is measured
PIM,down
with spacecraft’s output amplifier at its saturation point.
8.6.3 Illustrative test procedure
Two illustrative procedure examples for the PIM test are provided in Annex F. The PIM values can be
measured by two methods: with full wireless link setup or with wireless downlink setup. The procedure
to be used depends on the test requirement and whether the size of QZ can satisfy the full link setup.
9 Test report
A test report should include:
a) purposes and requirements of the test;
b) a reference to this document, e.g. ISO 23569:2021;
c) test procedures;
d) photos during the test;
e) chamber environment description;
f) test items;
g) test facility and measurement instrumentation;
h) test results and analysis on test error.
Annex A
(informative)
Illustrative procedures for EIRP test
A.1 EIRP test method with full link wireless setup
A.1.1 Overview
The spacecraft is installed on the DUT positioner located in the QZ. The Rx range feed is located at the
focus of the range reflector. The Tx range feed is near the Rx range feed.
The Tx range feed transmits uplink signal, via the range reflector to the QZ. The spacecraft Rx antenna
can receive the uplink signal, while the spacecraft Tx antenna can transmit the downlink signal. Then
the Rx range feed can receive the downlink signal. That is the full link wireless transmission route.
By using the value of received power measured by the Rx range feed in uplink saturation state, the EIRP
can be calculated.
A.1.2 Test schematic diagram
The EIRP test schematic diagram of full link wireless transmission route is shown in Figure A.1.
Key
RF signal line
boundary line divided range area
path loss line
Figure A.1 — EIRP test schematic diagram of full link wireless transmission route
A.1.3 Test instruments and equipment
a) Source: with AM modulation.
b) Spectrum analyser.
c) Power meter.
d) Fixed attenuator: with suitable attenuation.
e) Coupler.
A.1.4 Preparation before test
a) Spacecraft payload setup: correctly set the antenna beams, warm up the transponder’s operating
channels and make it work at fixed gain level.
b) Move the Rx range feed to the reflector’s focus for receiving and move the Tx range feed near
the Rx range feed for transmitting. Make the polarization of range feeds horizontal or vertical,
depending on the polarization of spacecraft antennas. If the polarization of spacecraft antennas are
linear polarization, the polarization of range feeds will coincide with the corresponding spacecraft
antenna’s polarization; if the polarization of spacecraft antennas are circular polarization, make
the polarization of range feeds horizontal.
c) Rotate the DUT positioner to make the spacecraft’s transmitting orientation to be tested (peak
point or typical point) coincide with NPA.
d) If the compact range has baffle or SERAP, move them to the correct positions, so that there is no
blockage of range feed beams, RF leakage to QZ, or illuminating at the nearby rim of the main
reflector.
e) Calibrate the range’s receiving path (from Rx range feed to power meter) and record the path loss,
L .
path, down
A.1.5 Test procedure
a) Based on link budget, set the RF source’s frequency and output power level (at least 20 dB lower
than the budget value) to make the payload work in linear mode, and monitor the readings of the
power meter.
b) Increase the source’s RF output power step by step until the uplink saturation point is reached.
Then record the readings of power meter.
A.1.6 Data processing
By calculating the EIRP according to Formulae (A.1) and (A.2), the EIRP for linear polarization in the
test point can be obtained.
QP=+LL+−G −30 (A.1)
EIRP Rx,,CR p,path down p,down Rx,CR
4πR
L =×20 log (A.2)
p,down
λ
down
where
Q is the equivalent isotropic radiation power, dBW;
EIRP
P is the power meter’s reading, dBm;
Rx,CR
L is the range receiving path loss (from Rx range feed to power meter), dB;
p,path,down
L is the equivalent range free space loss, dB;
p,down
G is the gain of the Rx range feed, dBi;
Rx,CR
R is the effective free space distance in compact range, m;
λ is the wavelength of downlink signal, m.
down
If the polarization of spacecraft Tx antenna is circular, a 0 dB to 3 dB compensation shall be added to the
EIRP since the range feed is in linear polarization. It is based on the antenna’s polarization properties.
By combining the EIRP value at the beam peak and the antenna pattern measured in subsystem level
EM/RM (radiation mock-up), the EIRP coverage pattern can be obtained.
A.2 EIRP test method with downlink wireless setup
A.2.1 Overview
The wireless downlink transmission route for the EIRP test means the spacecraft uplink is input by
cable directly. As done with full link wireless transmission route, the EIRP can be calculated using the
value of received power measured by the Rx range feed with the spacecraft in uplink saturation state.
A.2.2 Test schematic diagram
The EIRP test schematic diagram of downlink wireless transmission route is shown in Figure A.2.
Key
RF signal line
boundary line divided range area
path loss line
Figure A.2 — EIRP test schematic diagram of downlink wireless transmission route
A.2.3 Test instruments and equipment
As defined in A.1.3.
A.2.4 Preparation before test
a) Move the RF source near the DUT positioner and input the uplink signal by cable directly to the
spacecraft’s receiver.
b) Spacecraft payload setup: correctly set the antenna beams, warm up the repeater’s operating
channels and make it normally work at fixed gain level.
c) Move the Rx range feed to the reflector’s focus for receiving. Make the polarization of range feeds
horizontal or vertical, depending on the polarization of spacecraft antennas. If the polarization of
spacecraft antennas are linear polarization, the polarization of range feeds will coincide with the
corresponding spacecraft antenna’s polarization; if the polarization of spacecraft antennas are
circular polarization, make the polarization of range feeds horizontal.
d) Rotate the DUT positioner to make the spacecraft transmitting antenna’s orientation to be tested
(peak point or typical point) coincide with NPA.
e) If the compact range has baffle or SERAP, move them to the correct positions, so that there is no
blockage of range feed beams, RF leakage to QZ, or illuminating at the nearby rim of the main
reflector.
f) Calibrate the range’s receiving path (from Rx range feed to power meter), and record the path loss,
L .
path, down
A.2.5 Test procedure
a) Based on link budget, set the RF source at operating frequency and output power level (at least
20 dB lower than the budget value) to make the payload work in linear mode, and monitor the
readings of power meter.
b) Increase the RF source output power step by step until the uplink saturation point is reached. Then
record the readings of power meter.
A.2.6 Data processing
By calculating the EIRP according to Formulae (A.1) and (A.2), the EIRP for linear polarization in the
test point can be obtained.
If the polarization of spacecraft Tx antenna is circular, a 0 dB to 3
...