Úvod
Zařízení: N-P85-E0A8
Let ID: 1331Zobrazit události
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Datové sady
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Shrnutí letu
Výška
Apogeum
263.1 Metry
Čas do apogea
6.11 seconds
Výška vyhoření
65.73 m
Výška max. rychlosti
40.62 m
Výška vypuštění
112.22 m
Výška přistání
-3.33 m
Stabilita
Skóre stability
34.2 / 100 (Prúměrný)
Rozklad stability
Náklon při dohoření (20%)0
Stálost náklonu (15%)52.3
Klápění/zatáčení (30%)0
Tlumení (20%)76.6
Přímost tahu (15%)73.9
Rychlost
Max. stoupání
98.12 m/s
Max. klesání
-31.56 m/s
Při vyhoření
70.110 m/s
Rychl. přistání
-8.379 m/s
Rychl. klesání
-7.235 m/s
Rychl. vypuštění
71.51 m/s
Recovery
Single deploy (no dual deploy detected)
Zrychlení
Max. stoupání
23.65 G
Max. klesání
19.51 G
Max. při spalování
23.65 G
Prúm. stoupání
0.89 G
Prúm. spalování
10.66 G
Časy
Vyhoření (první)
1.12 seconds
Apogeum
6.11 seconds
Možné vypuštění
1.725 seconds
Přistání
42.05 seconds
Výstup #1 ZAP
0 seconds
Výstup #1 VYP
0 seconds
Úhly
Náklon rampy
2.70°
Max. náklon do vyhoření
36.19°
Klápění při startu
-1.64°
Klopní při startu
2.15°
Max. rotace (spal.)
2356.03 dps
Prúm. rotace (spal.)
1368.88 dps
Obecné
Datum nahrání
21-Mar at 10:16
Datové vzorky
2817
Celkový čas záznamu
57.300 s
Prúm. vzorký/s
49.1
Počet blokování
5
Výška záznamu
116.06 m
Start po zapnutí
1m 14s
Referenční osa
X
Baterie & teplota
Baterie začátek
0%
Baterie konec
0%
Teplota začátek
21.86°C
Teplota konec
14.57°C
Teplota MT1 start
0°C
Pravidla výstupu
Žádná pravidla
Animace dat letu
FLIGHT 1331
263.1 Meters
ALTITUDE
0.00m
VELOCITY
0.00m/s
ACCEL
0.00G
TILT
0.00°
PITCH
0.00°
ROLL
0.00°
YAW
0.00°
TIME
0.00s
AWAITING LAUNCH
ALT
altimetercloud.com
LAUNCH
T+0.00s
LANDING
BURNOUT
Motor burn complete
Poznámka: Animace letu vyžaduje montáž výškoměru v pevné orientaci. Kalibrujte senzory pro nejlepší výsledky.
Uživatelské poznámky
Přidejte toto zařízení ke svému účtu pro úpravy
Youtube video
Žádné video
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Obrázky letu (0)
Žádné obrázky
Propojená raketa
K tomuto letu není připojena žádná raketa
Informace o zařízení
Mercury V1
Tento let byl proveden na Mercury V1.
Verze hardware
Rev 1
Verze software
2.11
Naposledy online
21-Mar at 10:24
Akcelerometr
32G 3-axis
Gyroskop
2000 dgps 3-axis
Snímač tlaku
Bosch BMP 390
Magnetometr
N/A
Motory letu
1st Stage
1x
Klima
B4-4
Burn time
1.20 seconds
Diameter
18.00 mm
Average thrust
4.00 N
Max thrust
8.00 N
Impulse
5.00 Ns
Impulse class
B
Total weight
16.30 g
Propellant weight
5.40 g
Propellant type
composite
Links
Přidejte toto zařízení ke svému účtu pro úpravy
Místo startu, datum a čas
Klikněte na mapu pro označení místa startu. Přepínejte mezi mapou a satelitním pohledem.
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Klikněte na mapu · Přetáhněte pro úpravu
Lat—
Lng—
✓ Launch location saved successfully.
✗ Could not save location — please try again.
Pravidla výstupu
Pravidla umožňují Mercury provádět akce na základě podmínek letu. Každé pravidlo má až 4 podmínky (A-D).
Žádná pravidla
Přiřazení motoru (BETA)
Stále v testovacím režimu! Zjišťujeme, jaký motor byl použit.
Značka
Motor
Skóre
Tvar
Spalov.
Klima
B4
51
79.3%
81.3%
Quest
F41
49
65.1%
87.4%
AeroTech
E26W
48
74.1%
86.6%
AeroTech
H238T
40
9.3%
76.2%
RATT
HSM
39
12.9%
77.3%
Quest
E35
38
62.3%
86.1%
Cesaroni
143-G150-BS-13A
35
-5%
67.2%
Cesaroni
F36-SS
35
25.5%
80%
Loki
I405
35
9.4%
67%
AeroTech
D15T
33
4.8%
61.9%
Porovnání letú
Comparing against 8 other flights with the same motor configuration.
Highest apogee
The maximum altitude reached. Higher is better for altitude-focused flights.
263.1m|303.66 best2nd
Best stability
Composite score from tilt, spin rate, and ascent efficiency. 100 is perfect.
34.2/100|69 best7th
Fastest velocity
Peak ascent velocity recorded during the flight.
98.12m/s|115.87 best3rd
Best avg burn G
Average acceleration during motor burn, in G-force.
10.66G|10.66 best1st
Longest flight
Total recording duration from launch to landing detection.
57.3s|57.3 best1st
Lowest spin
Average spin rate during burn. Lower means a straighter flight.
1368.88dps|55.8 best7th
Coldest flight
Board temperature at launch. Cold conditions affect battery and sensors.
21.86C|8.44 best7th
Spalování motoru
Toto je velikost výstupu akcelerometru od startu do vyhoření.
You can check this against your motors thrust data on thrustcurve.org.
Obecná nastavení letu
Toto je snímek nastavení použitých pro tento let. Přejděte na
Přejděte na stránku Moje zařízení a nakonfigurujte nastavení..
Předpovězený tlak
i
Set this to your local forecast pressure at sea level. This will offer you slightly improved accuracty for your flight, although it's not 100% essential every little helps!
Xcweather.co.uk is a decent place to grab pressures from for your location and time.
Xcweather.co.uk is a decent place to grab pressures from for your location and time.
1013.2 mbar
Detekce startu
i
This is the altitude above the launch pad altitude where the altimeter will trigger itself into recording / flight mode.
The altimeter keeps a constant average of the pressure while waiting for launch, it uses a simple algorithm and the pre-flight buffers to do this. The most recent 120 samples (~4 seconds) are ignored so your pre-trigger altitude won't effect the ground baseline.
For almost all uses we suggest keeping this on the 25 Meter (~82 feet) default settings. If you want to test your altimeter by throwing it in the air, or are planning a very low flight you may want to lower the setting.
The altimeter keeps a constant average of the pressure while waiting for launch, it uses a simple algorithm and the pre-flight buffers to do this. The most recent 120 samples (~4 seconds) are ignored so your pre-trigger altitude won't effect the ground baseline.
For almost all uses we suggest keeping this on the 25 Meter (~82 feet) default settings. If you want to test your altimeter by throwing it in the air, or are planning a very low flight you may want to lower the setting.
10
meters
Sample ratio
i
The altimeter runs at 50Hz however you can record every sample or every X samples in order to extend the log time. For example if you set the ratio to 1 it will save 1:1 samples, or if you set it to 3 it will save 1 in 3 samples.
1:1 (50Hz)
Max samples
i
This is the maximum samples the altimeter will log per flight. When it reaches this amount it will stop and save the recording.
12000
Recording stop
i
This setting is how the altimeter decides to stop recording. You can choose either 300 or 600 samples stable or it will record until it's 10000 sample limit unless you press the BUTTON in Manual stop mode.
The samples stable method waits for the devices altitude not to change for the set number of samples. This is defined by not changing by more than +/- 1.0 meters for 98% of the samples, it's a reliable method to stop the recording after landing within 8-10 seconds (300 sample) or 16-20 seconds (600 sample).
The samples stable method waits for the devices altitude not to change for the set number of samples. This is defined by not changing by more than +/- 1.0 meters for 98% of the samples, it's a reliable method to stop the recording after landing within 8-10 seconds (300 sample) or 16-20 seconds (600 sample).
Auto: 300 samples stable
Oversampling
i
Oversampling is a internal setting of the BMP 390 pressure sensor. It is how many samples are taken for each reading. By taking multiple samples for each pressure reading the altimeter reduces noise and increases the resolution of the output.
The sensor can run at 50 samples per second in 4X mode, so we suggest leaving it in this mode as it will offer the highest accuracy.
The sensor can run at 50 samples per second in 4X mode, so we suggest leaving it in this mode as it will offer the highest accuracy.
8x Oversampling
IIR filter
i
The IIR filter is another internal sensor for the BMP390 pressure sensor. It is a Infinite impulse response filter used to enhance pressure measurement accuracy by reducing noise. It's primarily for smoothing out rapid pressure changes.
We suggest not setting this too high as it will cause delay to changes in altitude if set very high.
We suggest not setting this too high as it will cause delay to changes in altitude if set very high.
COEFF 7
Pressure filter
i
This filter is a software Kalman filter that runs on the altimeters processor.
The Kalman filter uses a prediction step based on a system model and then a correction step using new measurements to refine its estimate, it creates accurate most certain results from data with noise in it.
The Kalman filter uses a prediction step based on a system model and then a correction step using new measurements to refine its estimate, it creates accurate most certain results from data with noise in it.
Kalman 2 (default)
Lockout time
i
The Lockout time is how long the altimeter should stop making decisions and taking actions if it detects unusual high speed altitude changes that are unexpected.
These false readings can be caused by ejection charges (if the altimeter is in the same compartment as the motor ejection gases) or even when you transition to Mach speeds and can give false readings of altitude changes.
When these events are detected the system enters Lockout for the specified time while it stabalises. This effects things like triggering the output, or calculating other data.
These false readings can be caused by ejection charges (if the altimeter is in the same compartment as the motor ejection gases) or even when you transition to Mach speeds and can give false readings of altitude changes.
When these events are detected the system enters Lockout for the specified time while it stabalises. This effects things like triggering the output, or calculating other data.
750ms
Lockout change
i
This is how we detect a lockout. If the pressure changes by this much in a single sample downwards (pressure increase, lower altitude) then it's likely to be a false reading. Multiply the setting by 32 to get the speed in meters per second that it will trigger at.
1.5 meters
Sync sensors
i
The filters on the pressure sensor can cause it to lag very slightly behind the Accelerometer and Gyroscope data.
The Sync sensors option detects how far out of sync these sensors are. It then corrects the Acceleration and Gyroscope readings to match the pressure sensor.
AKTIVOVÁNO (18 samples / 351.00ms)
Orientation
i
This is the orientation you intend to install the Altimeter in your rocket. It's needed to ensure completly accurate angles and orientation charts and reports. Check out the Manual for more information on this.
Upwards (text up)
IMU filter
i
The IMU filter, or fusion filter takes the data from each axis of the Gyroscope and Accelerometer to calculate the Pitch, Roll, Yaw and tilt angle from vertical.
These filters can build up some discrepency over time so it's important to calibrate your sensors to minimise this.
Madgwick 6-Axis
Launch ALP
i
This is prevention against accidental launch detection.
With this disabled the launch is based only on pressure and something that creates a low pressure can trigger the flight by accident. For example pulling your nose cone off can even trigger it.
With this enabled the rocket also needs to have seen 8 samples (0.25 seconds) of acceleration above this setting in the last 3 seconds as well as the pressure drop to trigger. There is a backup trigger of 1.05 seconds of altitude being above the launch detect setting too.
There are very few situations where this option would cause issues, so we suggest leaving it on.
With this disabled the launch is based only on pressure and something that creates a low pressure can trigger the flight by accident. For example pulling your nose cone off can even trigger it.
With this enabled the rocket also needs to have seen 8 samples (0.25 seconds) of acceleration above this setting in the last 3 seconds as well as the pressure drop to trigger. There is a backup trigger of 1.05 seconds of altitude being above the launch detect setting too.
There are very few situations where this option would cause issues, so we suggest leaving it on.
1.4G
Launch lock
i
When enabled, the altimeter locks out recording for a set period after power on to prevent false triggering during setup.
DISABLED
Static temperature
i
A fixed temperature value used for altitude calculation when the external temperature sensor is disabled or not connected.
15.00 °C
Temp sensor
i
If an external MT1 temperature sensor is connected, this controls whether it is used for logging only or also for altitude calculations.
DISABLED
Nastavení výstupu
Toto je snímek nastavení použitých pro tento let.
Výstup 1 aktivní
i
Disable or enable the output from being able to turn on or off.
DEAKTIVOVÁNO
Výstup 1 spouštěč
i
After apogee (altitude)
This method triggers when the altitude drops below the set altitude after apogee is detected.After apogee (time)
This method triggers the defined seconds after apogee is detected.After launch (altitude)
This method is activated if/once the altimeter exceeds the set altitude after launch.After launch (time)
This option triggers the defined seconds after launch is detected.After burnout (time)
This method triggers the defined seconds after burnout is detected.
After apogee (altitude)
Výstup 1 doba zapnutí
i
This is how long the output should trigger ON state when the rules are met.
2000ms
Výstup 1 výška
i
This is the altitude to trigger at if using a trigger method that works on altitude.
For example if you set this to 75m and After apogee (altitude) for the trigger then the output will turn on at 75m on descent above the launch altitude.
For example if you set this to 75m and After apogee (altitude) for the trigger then the output will turn on at 75m on descent above the launch altitude.
0 meters
Výstup 1 čas
i
This is the time variable for output triggers that work on time.
For example if you set this to 3 seconds and After apogee (time) as the trigger then the output will turn on 3 seconds after apogee.
For example if you set this to 3 seconds and After apogee (time) as the trigger then the output will turn on 3 seconds after apogee.
0 seconds
Zámek výšky
i
Altitude lock is a safety feature that prevents the output from triggering if the altitude is below this level when the rules are met.
50.00 m
Zámek úhlu náklonu
i
This is another safety feature. It can be used to disable the output if the rocket has gone too far from vertical.
For example if you set the tilt angle lock to 40 degrees then the output will not fire if the rocket is more than 40 degrees from vertical. To disable set this to 0.
For example if you set the tilt angle lock to 40 degrees then the output will not fire if the rocket is more than 40 degrees from vertical. To disable set this to 0.
0.00 °
Kalibrace senzorú
Kalibrační offsety použité pro tento let.
Gyroskop
⚠ Gyroskop nebyl zkalibrován
X
0.000°
Y
0.000°
Z
0.000°
Akcelerometr
X
9.530 mG
Y
-9.880 mG
Z
45.610 mG
Nastavení zařízení
Toto je snímek nastavení použitých pro tento let.
Toto je snímek nastavení použitých pro tento let.
TAG zařízení
i
A custom name or tag assigned to this device for easy identification.
Merc9348
Jazyk
i
The language setting configured on the device.
en
Režim vypnutí
i
Controls what happens after recording. Standard shuts down normally, Delayed keeps WiFi on for 30 seconds after landing, Stay on keeps the device powered on.
Delayed 30s
Jas LED
i
The brightness level of the LED indicators on the Mercury. Lower values save battery.
20%
WiFi TX power
i
WiFi transmit power level. Higher gives better range but uses more battery.
8 dBm
Režim spánku
i
Controls whether the device enters low-power sleep when idle.
Normal (sleep when idle)
Monitor baterie
i
Monitors battery voltage during the flight.
DISABLED
Cloud group
i
The cloud group / category this flight is assigned to.
Altitude record attempts (B impulse)
Porty GP6 / GP7
Konfigurace portů GP6 a GP7 pro pyrokanály, serva nebo jiná zařízení.
Channel 6 mode
ON = HIGH
Ch6 min pulse (µs)
1000
Ch6 max pulse (µs)
2000
Ch6 frequency
50 Hz
Ch6 angle ON
170.00°
Ch6 angle OFF
10.00°
Ch6 on time
2.00s
Channel 7 mode
ON = HIGH
Ch7 min pulse (µs)
1000
Ch7 max pulse (µs)
2000
Ch7 frequency
50 Hz
Ch7 angle ON
170.00°
Ch7 angle OFF
10.00°
Ch7 on time
2.00s
Deska servo I2C PCA9685
Toto je snímek nastavení použitých pro tento let.
Configuration for the external I2C PCA9685 servo expansion board. This board provides up to 6 additional servo channels.
No I2C servo board was connected for this flight.
Predikce a vzdušné brzdy
Toto je snímek nastavení použitých pro tento let.
The Mercury can predict apogee while coasting after burnout. These settings control the prediction calculation and optional air brake system.
Dry mass
i
The total mass of the rocket after motor burnout (dry mass). This is used for the ballistic prediction of apogee altitude. Enter the mass without the motor propellant, or the mass at burnout.
0.1500 kg
Drag Cd
i
The aerodynamic drag coefficient (Cd) of the rocket. This is used with the rocket area to calculate aerodynamic drag during coast. A typical model rocket has a Cd of 0.4 to 0.8. You can find this value from OpenRocket or RockSim simulations.
0.750
Reference area
i
The cross-sectional reference area of the rocket in square meters. This is typically the area of a circle with the body tube diameter. For example a 38mm tube has an area of approximately 0.00113 m².
0.00100 m²
Gas constant
i
The specific gas constant for dry air, used in the atmospheric model for altitude and density calculations. The standard value is 287.05 J/(kg·K). You shouldn't need to change this unless you know what you're doing.
287.05 J/(kg·K)
The following settings configure the air brake system.
Air brake enabled
i
Enables or disables the active air braking system. When enabled, the Mercury will deploy air brakes via the configured servo channel to try and reach the target altitude. Firmware 2.1+ required.
OFF (default)
Servo channel
i
Which servo output channel the air brake mechanism is connected to. GP6 and GP7 are the two onboard servo headers, I2C channels are for an external servo expander board.
GP6
Deploy speed
i
The speed at which the air brakes deploy. The Mercury gradually increases the servo angle until the predicted apogee matches the target rather than going full on/off. This setting controls how quickly it ramps up to full braking.
Medium (default)
Target altitude
i
The target apogee altitude in meters. The air brake system will try to slow the rocket so it reaches this altitude.
300.00 m
Over shoot %
i
The percentage over the target altitude to aim for until within 15% of the target. This helps prevent undershooting if the prediction is slightly off early in the coast. For example, with a 1000m target and 5% early adjustment, the Mercury will aim for 1050m until it passes 850m.
5.00%
Activation altitude
i
The air brake system activates after burnout, but won't engage until the rocket has reached this percentage of the target altitude. This prevents the brakes from deploying too early when predictions may be less accurate.
20% (default)
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