MR60

Well ... at least until the next discovery.

(sorry about the delay on this post ... the site was down for quite a while)

Definitions.

-          FCU is the Flight Control Unit (e.g., Pixhawk or APM).

-          VDEP is the Vibration Dampened Electronics Platform where the FCU and other electronics are attached (including a gimbal/camera).

-          Ship attitude is the pitch and roll angle relative to time of the 2-dimensional plane(s) formed by lift from multirotor ships (e.g., the lift-plane formed by the four lifting propellers of a quad).

-          Latency is the delay caused by the time it takes for an attitude change of the ship to reach the FCU, for the FCU to process the change, for the FCU to appropriately command a change in rotor thrust, for the rotors to react, for the rotors and frame to change momentum, and for the attitude of the ship to create a controlled change.

-          Noise is the part of a signal that is random and should be ignored when analyzing ship attitude. Noise is that part of a signal that contains vibrations (up and down movements) that are too high in Hertz for a multirotor response and because these vibrations self-reverse, do not require attitude correction. In fact, correction in many cases would make the ship less stable. Significant causes of vibration noise are:

  • The imbalance of props,
  • The imbalance of motors,
  • Motor mast harmonics or flex (not stiff enough),
  • Propeller harmonics or change in Angle of Attack at different RPM.
  • Prop wash exciting  the rotor spar or VDEP,
  • VDEP harmonics (not stiff enough),
  • External systems (e.g., a camera gimbal that resonates at specific angles or speeds).

-          Attitude Error is the difference between actual ship attitude at time t and the attitude perceived by the FCU at time t. Differences are caused by latency and lack of ship rigidity between the lift-plane and FCU.

-          Damping, in this discussion, is measured by the reduction in the amplitude of noise going to the FCU without causing attitude error and a resulting loss in flight control. A true damper reduces vibration noise by decreasing the amplitude (force) of that vibration (turns part of the energy causing the amplitude into heat or another energy form) but does not increase attitude error. Damping increases the signal to noise ratio between actual ship attitude and the FCU at any given time t.

-          Isolation, in this discussion, is measured by the reduction in the amplitude of noise along with the increase in attitude error. Because it is important that the FCU know the attitude of the multirotor, damping is good and isolation is bad.

Background.  This is the history as I know it.

-          A multirotor weighing more than 300 grams can only respond with significant thrust deltas in the 20 or less Hertz range (see other research I produced testing actual lift response rates on various size ships). Thus vibration noise is typically greater than 5 to 20 Hz, depending on the ship and the FCU is effectively responding to attitude changes occurring at less than 20 Hz.

-          A Pixhawk flight controller is still delivered with optional mounts make of foam.

  • On poorly designed ships (loose), the foam pads help prevent flight run-aways
  • On ships designed well (stiff), the foam pads were proven to increase vibration (increased latency and caused harmonics).

-          To prove the negative impact of dampers on the FCU, I developed the open source Hover Analysis worksheet that:

  • Automatically finds the best hover of an attempted sustained hover flight.
  • Shows vibration levels in x (roll), y (pitch), and z (elevation) axis.
  • Shows the watts required to hover.
  • Shows IMU (gyro and acceleration sensor) health.
  • Suggests the optimal throttle setting.
  • Suggests the optimal roll and pitch balance setting.
  • Shows the impact of damping versus isolation.
  • Invited ship builders/modifiers to take the vibration test. All that did, found that removal of foam, pads, elastic bands, etc. reduced FCU vibration levels and at the same time increase attitude control (reduced isolation).
  • All cases of vibration reduction using elastics that were found to reduce FCU vibration also greatly reduced attitude control (e.g., caused isolation, not good when trying to control ship attitude).

 

An example of the issue with was demonstrated by Keven on one of his ships, shown below. Note the serious inability of the FCU to control the ship with latency caused by tape or moon gel.

Figure 1. Adding Dampers & Isolators Onto A Stiff Frame

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-          I was a strong and vocal advocate of:

  • Only using dampers between the ship and camera gimbal but not between the rotor and FCU. The gimbal doesn’t control the ship so it is OK to isolate it. The FCU controls the ship, so it should not be isolated.
  • Hard fixing the FCU to a stiff rotor frame.

 

Then I discovered the Frantz Strut, a fortuitous accident, while trying to prove that dampers have no place on a light, well-engineered ship ... resulting in proving that I was one again … wrong. Oh well J  

Physics of Vibration (Noise):  So what is the Frantz Strut? First, a little physics on vibration control. The following are well known ways to passively control vibration:

1)      Let the vibration wave hit something dense on its way to the FCU, so the dense object will reflect the wave in a manner that allows the reflected wave to cancel other incoming waves. This approach in general does not work on multirotors as a primary approach because adding a denser object between the rotor and FCU adds weight … causing the rotors to work harder … increasing the amplitude of the source vibration wave (and flight times are shortened). But does this really work? If the ends of a rotor spar are relatively fixed, the reflected wave (wave (b) below) is an inverse of the inbound wave (wave (a) below) and can interact with inbound waves of a similar frequencies … partially nullify them (the sum of two inverse identical waves that are overlaid is a cancelled wave (see example t2 in Figure 3); similar to how noise cancelling headphones work, but this is accomplished passively, not actively).

Figure 2. Reflected Wave

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Figure 3: Interaction of a Red and Blue Wave forming a Compound Wave

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2)      Find and attach to the node point of the vibrating rotor spar (the node is where the amplitude = 0). A tube when vibrating may have a portion of the vibration (frequency ranges) that causes the bar to oscillate (bend) in full, half, third, quarter (etc.) waves as the vibration excites and permeates through the rotor spar.

Figure 4: Exaggerated Nodes and Harmonics

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3)      Find a damper that dampens but does not isolate. Every scientist that I contacted that does damping professionally told me that materials do not exist that can dampen light objects (the FCU only weighs about 40ish grams and less if you remove the covers).

4)      Add mass. Mass is a great dampener and unless the engineer really screws up, does not isolate.  Double the mass and amplitude is cut in half. If the FCU weighs 20 grams and it is bound to a battery weighing 220 grams, then the amplitude of the FCU will be cut by (220 + 20) / 20 or a factor of 12.

Amplitude = -kx / mass

5)      Objects vibrate proportionally to the force acting on them and inversely proportional to the object’s stiffness.

Vibration = Force / Stiffness

 

The Frantz Strut – How It Works:  Enough BS … quit delaying, what is the frackin’ Frantz Strut? The Frantz Strut is a device can weigh less than 20 grams total that takes advantage of all five of the methods that have an a passive impact on vibration (noise to the FCU).

1)      It uses a small but denser (silicone, rubber, or plastic) damper or damper housing between the carbon rod that holds the rotors and the VDEP/FCU.

2)      It firmly attaches a housing to the node point on the rotor spar in order to transmit a minimal portion of the vibration energy.

3)      It embeds the damper inside the housing that dampens the energy between the housing and axle leading to the VDEP/FCU. The damper is such that it can dampen noise (small higher-frequency amplitudes) but transmit even small deltas in ship lower-frequency attitudes with insignificant latency.

4)      It puts the battery weight and non-rotor weight on the VDEP with the FCU so that not only is the mass greater (lower amplitudes) but the damper can now work against a greater load, making the damper material more viable and useful. It should be noted that on really light VDEPs that the damper serves no use (the axle is attached directly to the node points on each rotor spar).

5)      It uses a stiff rotor spar to keep the source magnitude of vibration low and to aide in vibration reflection when noise waves hit a denser damper. Vibration are in the x, y, and z direction, so:

  1. A carbon tube is the most optimal free-span material.
  2. A carbon I-beam is the most optimal side-supported material.

 

The drawing below shows:

-          The rotor

-          The rotor spar (the larger circle; looking down its axis) that is stiff relative to the vibration force.

-          The damper housing (the odd shaped object that contains both circles) that retains a damper and firmly grips or is bonded to the rotor spar at two of the spar’s vibration nodes.

-          The damper is not shown but it is retained by the damper housing, surrounds and is concentric to the VDEP axle in a manner that puts a damping material between the housing and VDEP axle (the small red-dashed circle). The damper is selected so it can respond to x, y, and z vibrations of the energy levels of the rotors and mass of the VDEP.

-          The VDEP axle (the small red dashed circle; looking down its axis) that is fixed to the VDEP. Each axle is suspended by two dampers.

-          The VDEP spans from center to center of both axles (the line coming from the lower left of the drawing, maintaining a space around the rotor spar, and continuing vertically; also see the top-view). The VDEP must maintain a space around the rotor spar in excess of vibration amplitudes and VDEP flight mass movements. Shown below is a 1,27 mm gap (0.050”).

Figure 5: Simplified End-View of the Frantz Strut. 

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The Frantz Strut is shown in the Top View (Figure 6) in the two sets of red dashed lines: the fore and aft strut each consisting of 2 housings, 2 dampers, and an axle that is bonded or fixed to the VDEP. The basic design of the ship can be regular, spider, H, coaxial or a variant like below. All that is added (at most) is a damper housing, damper, and axle for a fore and aft strut that is attached to the VDEP.  In the drawing below, the fore spar, aft spar, and crossbar do not touch the VDEP. Only the fore and aft axle hold the VDEP. The axle does not need to be nearly as stiff as the rotor spars. The optimal span of the axle depends on the ship (varies from about 50% to 100% of the motor span), but most ships will find that the optimal span is locating the housings close to the motors.

 

Figure 6: Top View of a Quad with the Frantz Strut

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The Frantz Strut – Performance:

-          An FCU will only control objects with any degree of reliability that have vibration noise less than 0.5 gs (gravity equivalents) of force (a measure that is directly proportional to amplitude).

-          A good “score” of vibration noise is between 0.10 and 0.20 gs.

-          When building ships that used hard fixed FCUs on stiff frames to partially isolated FCUs on gel or other isolation method, the best scores derived were between 0.06 to 0.10 gs.

-          The following is one of four ships build (by various folks) tested so far of different size and configurations that all derived a similar scores of between 0.03 to 0.04 gs using the Frantz Strut.

-          Also note that excellent signal to noise ratio proxies were factors of 2 to 5. The ship example below has a signal to noise proxy of nearly 10, easily twice as high as previous bests.

 

Figure 7: Frantz Strut Vibration

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In addition, the measure of flight control also scored excellent, even while flying in the man-cave, trying to avoid decks and chairs. I’ll update this picture later after I take time to tune the ship with a "free" hover outside. But, there were people waiting for the test results so …

 

Figure 8: Attitude Control Using the Frantz Strut

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How To Build It: “I don’t have the test equipment that you have, so how can I possibly build one?”

It is actually extremely easy as there are only three different parts and two are off the shelf. Your system might not be optimal, but it will have excellent performance and fly just great. The parts list is:

-          Housing for the Damper. It can be made:

  • From
    • Carbon/Balsa sandwich panel (the lightest approach)
    • Printed plastic (ask  if a certain person will share their print file or CAD drawing)
    • CNC’d plastic
  • To fit
    • An H frame (axle is parallel to the fore/aft rotor spars)
    • An X or V or regular frame where the damper retainer is at an angle or can swivel to the axles that can still be perpendicular to the VDEP but at a non-right angle to the spars.

-          Damper is off-the-shelf. Depending on the ship mass (if you don’t have the test equipment, use the Charmin squeeze test).

  • GoPro size for < 400 gram ships
  • Medium size for > 400 gram ships

-          Axle is an off-the-shelf carbon tube that is sized to fit through the center of the damper.

The assembly is:

-          Insert the damper into its damper housing (assemble four).

-          Clamp or bond the housing to the stiff rotor spar at the maximum or optimal span.

  • Two housings fore
  • Two housings aft
  • Max span for many ships will be the ideal location (but not always)

-          Insert the axles through the center of the damper pairs (one pair fore and one pair aft) and either through the VDEP or attached to the VDEP

The entire system will weigh about 15 to 20 grams if made from carbon and less than 45 grams total if the housing is printed from plastic.

I also invite other team members to add their photos and results of the ship they built using the Frantz Strut sharing their unique methods of implementation.

The following shows an aft video of the Frantz Strut working.

https://youtu.be/cHDM2Ql5_aw 

I’ll post photos later.

Developers and Manufacturers of Ships and Ship Parts: This discovery has been made public. You may use it freely use it without royalty. I only ask that you give credit where due. Hopefully as this discovery becomes widely known and proven that this discovery will be recognized and worth advertising as a feature of your commercial ships. From the data above, developers should be able to achieve 80% of the improvement potential of the Frantz Strut.  A significant improvement for most applications.

I will protect data and test methods not disclosed here for how to optimize the design of the Frantz Strut where the remaining 20% of reduction is significant to specific applications by:

-          Minimizing vibration at the VDEP.

-          Maximizing the signal to noise ratio of ship attitude at the FCU in real time.

 

Postscript. Now that ship vibration and the camera gimbal have been optimized, I can finally get back to:

-          Learning FPV (and when legal, long-range FPV)

-          Completing the optimal camera/sensor ship (started last year but distracted by learning to build an optimal gimbal and solving vibrations).

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Replies

  • hi again :) general view of quad. Slightly V-frame like TBS

    3702324595?profile=original

    3702325179?profile=original

    3702325221?profile=original

    damper mounts repeat damper balls geometry and fix it securely

    3702325256?profile=original3702325146?profile=original3702325322?profile=originalyesterday i replace stiff dampers to soft 100g rated, and rreinforced frame gluing attachment to the frame beams acetone

    fly and read logs. here it.

    3.3 style vibration logs

    3702325274?profile=original

    and 3.1 style. XY beetwen 0.5! hooray :)

    3702325248?profile=original

    and spreadsheet result

    3702325348?profile=original

    Forrest can you tell where i can see in spreadsheet this item

    o Determine if Pitch and Roll PIDs need to be different (if their stabilities differ, maybe)

    thanks!

  • MR60

    Alexey - Nice work. Good experiment. Great results.

    Looks really cold there in Russia.  Can you share photos of the:

    - Ship

    - Housing for the damper

    - Attachment of the damper housing to the motor spars

    Would love to see how you solved those design challenges.

  • ?width=400

    My version of vdep bases on damping balls.

    ?width=400

    I try 2 sets of balls.

    1. 100g per pcs from hobbyking 

    2. xg per pcs from storm32 3axis gimbal from goodluckybut. This dampers more stiff. I dont know they weight rating.

    So i test vibrations

    First dampers

    ?width=600

    second

    ?width=700

    Soft dampers win :)

    and log from Forrest Frantz spreadsheat

    3702324753?profile=original

    I understood correctly that my FC accelerometer  is not correctly calibrated? And i need to recalibrate it or use AHRS_TRIM as shown in table? Spreadsheed can recognise bad calibration of accelerometer?

    Unfortunately the video is not as stable as i would like

    soft dampers

    https://youtu.be/WecKx4bvMcE

    stiff dampers

    https://youtu.be/wrluwtQpyaU

    I will return soft. Picture with this dampers is better.

    Weight of VDEP approx 600g

  • Well, its always best to resolve the source of vibration if possible. Easiest thing to try first is the motor/prop balance...

    https://www.youtube.com/watch?v=lF8-KqG6gcM

    YouTube
    • Cool Hellcat, thank's for share, wait Forrest tests.

      • Hi guys

        Thought I would chime in here as there is some interest in our products. Yes, we have a new product called "Impulse" which has refined hardware. The video's should hopefully explain the process. We also encourage users to perform frequency analysis to help determine root cause behind mechanical faults such as imbalance, misalignment, bearings, loose fittings etc.

        For most balancing applications you only need 1 accelerometer. However if you are performing 2 plane balancing such as a turbine, then you will need 2 accelerometers and 1 IR sensor.

        Our products have been in the market for some time now and we are improving its capability over time. We aim for a cost effective solution for modelling applications without the huge price tag.

        Off course we are happy to answer any questions. Feel free to email us.

        enjoy!

        • MR60

          Do you recommend that each "motor w/o prop" and then "motor w/ prop" be tested as mounted on the ship (assuming that the ship can be secured w/o impeding vibrations on the rotor spar) or on a test platform?

          • Nice work and application on the Frantz strut.
            I agree on the need to balance and remove as much source vibration as possible. I always started with a balanced prop and motor combo then running each up individually. Turning the prop 90deg at a time on the motor and adding/removing tape weight is also required. A very time consuming process but the results were very favorable flight stability.
            I've seen this "strut" application also used on rifles barrels to reduce vibration and bad harmonics for increased accuracy.
            • MR60

              cool on the rifles ...

              like you, I've also gotten to finding and marking the correct orientation for the T type props and also documenting the orientation in case the mark wears off.

          • Generally we follow that process, i.e. Balance "Motor" first then "Motor + prop". The reason why is due to the fact that the prop may not be the root cause it could be the prop adapter. Sometimes I've been trying to balance a prop with little success. After analysis I found the adapter was slightly misaligned. After correcting the issue and then balancing the prop all was good again :)

This reply was deleted.

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