Goose CS-110 is a fully unpowered interceptor round, thrown from a ground tube on shop air at 189.2 m/s and flying a ballistic arc on six fixed fins. This page is the round itself: every part, every station and every figure the design closes.
Goose CS-110 is a pneumatically launched, fully unpowered kinetic interceptor. It leaves a ground tube on shop air, flies a ballistic arc, and defeats a small uncrewed aircraft by collision.
The round is a solid steel nose on a moulded glass-filled nylon airframe: 1.600 kg all-up and Ø90.00 mm across the obturator. It is indexed into the breech, thrown by air, and from the muzzle onward it is on its own. Nothing on it is powered and nothing on it is armed, because there is nothing to arm.
That is the design position, and it is a short list of absences. The round carries no battery, no motor, no receiver, no servo, no sensor, no indicator and no initiator, and so it carries no wiring of any kind. It carries no warhead, no fuze, no primer, no propellant and no energetic material. Nothing on this line transmits by radio and nothing guides on a link, and on this round that doctrine costs nothing to hold: there is nothing aboard for an adversary to reach into. Guidance on this line sets out the three tiers and where each program sits.
What throws the round is ground equipment with its own page — the launch platform holds the accumulator, the breech and the tube. What goes on the front is a subject of its own again, at heads and the nose interface. The loop they run together, cue to reload, is the engagement, and the line sits behind CDNS UAV Platforms. This page is the round.
Powered flight was priced at this mass before it was set aside. At 1.6 kg a round this size cannot carry the battery that sustained flight would need.
Powered flight was priced for a 1.6 kg body held at the speed a launch tube gives it, and the conclusion in the engineering is flat: the round cannot carry the battery. Small bodies pay a punishing price for speed, and every gram of pack, motor, controller and wiring comes straight out of the part that does the work at the far end.
So the round spends nothing. The accumulator does the work once, inside the barrel, and hands the round 28.64 kJ at the muzzle. After that the only forces on it are gravity and drag, and the only authority over its attitude is the geometry it was moulded with. The same arithmetic that closed powered flight at 1.6 kg opens it further up the mass scale, in a separate class with its own bore and its own tube: CS-120 carries a motor, a battery and a flight computer at 15 kg.
Unpowered is not a stripped-down powered round. It is the decision that lets this one be five parts, an adhesive and a steel slug.
Count the round and the answer is five moulded or machined parts and one structural bond. That is the whole bill of material, front to back.
Item 1101 is the nose slug, machined from AISI 4140 in the normalized condition, 41.0 mm deep and presenting a flat Ø70 face. Item 1201 is the forward body shell, 120.0 mm of moulded PA66-GF33 at Ø70.00 mm. Item 1301 is the tail boom, 260.0 mm at Ø32.00 mm. Item 1401 is the fin, moulded six off. Item 1501 is the obturator cup, 12.0 mm thick, the part that takes bore pressure across the full Ø90.00 mm and pushes everything ahead of it up the tube. The sixth line on the bill is a two-part structural epoxy.
Those five parts are the round, nose to cup, and the build runs in the same order. The nose is set into the forward shell. Shell and boom are bonded across the transition cone. Six fins go into their boom lands in a jig. The obturator cup goes on last. Two acceptance gauges sit at the bench, and the fin bond is not accepted until each of the six reads 60° ± 0.5°.
The moulds are the product on this line, cut in-house; the reasoning sits on the manufacturing page.
The budget closes on 1.600 kg. Four of the five lines are the airframe, and together they are less than a quarter of the round.
A round is a mass argument before it is anything else. Every gram in the airframe is a gram not arriving at the target, so the budget is written to push mass forward into the one part that does the work and hold everything behind it to the minimum the structure allows. The forward shell, the boom, the six fins and the obturator cup together come to 368 g. Everything else is nose.
| Item | Part | Material | Mass |
|---|---|---|---|
| 1101 | Nose slug | AISI 4140 normalized | Most of the all-up mass |
| 1201 | Body shell, forward | PA66-GF33 | 89 g |
| 1301 | Tail boom | PA66-GF33 | 84 g |
| 1401 | Fin set, six off | PA66-GF33 | 88 g · 14.7 g each |
| 1501 | Obturator cup | PA66-GF33 with a TPU or filled PTFE land | 107 g |
| — | All-up mass | Five parts and a structural bond | 1.600 kg |
The mass budget as the design closes it, with the nose carried as the largest line.
The table carries one reading, and the rest of the round follows from it: the round is mostly nose by mass, the airframe is a carrier, the steel is the effect, and there is no chemistry anywhere in it.
One machined slug of AISI 4140 in the normalized condition, 41.0 mm deep behind a flat Ø70 face, is three quarters of the round and the whole of what it does at the far end.
The nose is not strength-critical. It is a mass item, and it is chosen as one: AISI 4140 normalized, ultimate tensile strength around 655 MPa, density 7,850 kg/m³, to ASTM A29/A331 as the reference the machining works to. Steel is chosen for density in a bore of fixed diameter. Nothing about the nose is asked to be clever; it is asked to be heavy, to be square to the axis, and to seat on the one mechanical interface every head on this line mounts to.
That last point is what makes the line work as a line rather than as three separate rounds. Every head mounts to the same interface, the capture round is held to the kinetic round's 1.6 kg, bore and magazine pitch, the launcher delivers the same 30 bar over the same 3.00 m stroke to either, and one magazine can index a kinetic round and a capture round in the same belt. The mechanical detail of that joint — a Ø64.9 spigot register, a Ø70 shoulder and a three-lug bayonet, and not one conductor across it — is set out at heads and the nose interface.
The effect at the target is collision, and collision is all of it. There is no explosive train anywhere in this round, no initiator, no primer and no propellant, and pneumatic launch means there is no propellant on the magazine either. The steel arrives at speed, and the speed came from air.
The moulded shell is 2.50 mm thick. Strength alone would allow 1.19 mm; buckling under the launch stroke demands 2.14 mm, and moulding practice rounds it up from there.
Two failure modes were carried side by side at a safety factor of 2.0, and buckling governs the shell by roughly 1.8× over material strength. That is the ordinary result for a thin moulded tube pushed hard from behind: the wall is not going to be crushed, it is going to fold. Conditioned PA66-GF33 needs 1.19 mm to carry the axial load and 2.14 mm to stay stable under it, so 2.50 mm is selected and the extra goes to a wall thickness a mould tool can hold consistently.
At the critical station, just ahead of the cup, the shell carries the whole round at peak acceleration, 18,191 N in axial compression, and it is buckling that decided the wall.
Axial compression. Conditioned PA66-GF33 at 50% RH asks for 1.19 mm of wall to carry the axial load at a safety factor of 2.0. Material strength is not the constraint on this shell.
Shell buckling. Stability under the same load, at the same factor, asks for 2.14 mm. This is the mode the wall thickness is chosen for, and it is why the shell is thicker than a strength calculation on its own would ask for.
The body does not run at bore diameter to the tail. It steps from Ø70 to Ø32 across a 30 mm cone, and the slim boom that follows carries the highest shell stress in the round.
Two requirements pull the aft end in opposite directions. The stability solve wants a long moment arm behind the centre of gravity, and the fins want span. A body at bore diameter leaves the fins no span, and the round tumbles. Stepping down to Ø32 gives them the span the stability solve asks for while the transition cone keeps the load path continuous through the diameter change.
The step is paid for in stress. At Ø32 with the same 2.50 mm wall, the boom carries the highest shell stress in the round, and it sits, deliberately, in the cheapest and most easily replaced moulding on the bill. The load it is holding is the full peak base force of the launch, applied at the obturator cup behind it and carried forward through the boom into the body and the nose.
| Station | Figure | What sets it |
|---|---|---|
| Bore and obturator OD | Ø90.00 mm | The tube. Bore area 63.617 cm². |
| Main body OD | Ø70.00 mm | The stability solve. |
| Tail boom OD | Ø32.00 mm | The fin span requirement. |
| Shell and boom wall | 2.50 mm | Buckling, rounded to moulding practice. |
| Transition length | 30.0 mm | The Ø70 to Ø32 cone. |
The principal stations of the round, each one carrying the reason it is that number.
Six is the answer the stability solve gives. Four does not close and eight is over-stable. They are bonded into lands in the boom, and there is no cam, no trim tip and no servo anywhere on the round.
Each fin is a moulded PA66-GF33 blade with a 120.0 mm root chord, a 60.0 mm tip chord at a taper ratio of 0.5, 4.00 mm thickness and 25.0° of leading-edge sweep. The six weigh 88 g together, 14.7 g each.
They are bonded, not hinged. Six lands are moulded into the boom, the fins are set into them in a jig, and the bond is checked at 60° ± 0.5° before it is accepted. From that point the round's aerodynamic configuration is frozen in the part. Fin alignment is an acceptance check at the bench and never an active trim in flight, and the round leaves the muzzle with its attitude decided by geometry alone.
The division of labour is clean and it is the reason the round can be this cheap. The launcher aims: it holds the boresight offset, computes the laying solution and drives the mount to a solved azimuth and quadrant elevation. The round flies ballistic. Nothing at the muzzle bends anything, and nothing in flight is asked to.
The gap between the centre of gravity and the centre of pressure is the static margin, and on this round it sits inside the 1.5 to 2.5 calibre band the design works to.
A heavy nose and a long tail is the oldest stability trick there is, and this round is an unusually pure example of it. Most of the mass sits in the steel nose, which puts the centre of gravity well forward. The fin set at the far end of the boom puts the centre of pressure well aft. The difference is the static margin, and it sits inside the 1.5 to 2.5 calibre design band.
Too little margin and the round is loose in pitch and yaw off the muzzle. Too much and it weathercocks into the crosswind and throws the laying solution away. Sitting near the middle of the band matters more on an unguided body than on a guided one, because there is no loop downstream to absorb what the airframe gets wrong. Six fins rather than four is part of the same answer: four does not close the solve at this mass distribution, and eight puts the round over-stable at the top of the band.
A fixed accumulator volume expands into a growing barrel volume behind a cup that spans the full bore. The stroke puts 28.64 kJ into the round.
The model behind these figures is an isentropic expansion of a fixed accumulator volume into the growing volume behind the round, integrated as a two-state differential system with a valve-opening ramp and constant seal drag, at a ratio of specific heats of 1.40. The obturator cup takes full bore pressure across Ø90.00 mm — 63.617 cm² of area — and pushes the round up the tube ahead of it. Charge pressure is 30.0 bar, which is shop-air class and deliberately so, and the stroke is 3.00 m.
| Quantity | Figure | Note |
|---|---|---|
| Charge pressure | 30.0 bar | Shop-air class. |
| Stroke | 3.00 m | Ø90.00 mm bore, 63.617 cm². |
| Accumulator volume per shot | 15.9 L | After the gas-inertia correction. |
| Muzzle velocity | 189.2 m/s | The exit figure the model closes on. |
| Muzzle energy | 28.64 kJ | Into a 1.600 kg round. |
| Combined energy efficiency | 85.9% | Calculated from five named losses against the ideal expansion. |
| Largest single loss | Gas inertia, 5.2% | The charge air is accelerated with the round. |
Interior ballistics for the round as the engineering closes them, at 30.0 bar over a 3.00 m stroke.
Two of those lines matter commercially rather than technically. The 15.9 L per shot is what an accumulator has to give back before the next round can go, and recharge, not the tube, is what sets the tempo of a launch line — that argument belongs to the launch platform. And 85.9% combined efficiency is what decides how much compressor a launch line needs standing behind it.
Both figures are the round's, and they are not interchangeable. The mean describes the stroke. The peak arrives in the first fraction of a millimetre and every part on the bill is sized against it.
Peak acceleration is 11,369 m/s², or 1,159 g, at x = 0 and t = 0.14 ms. Mean acceleration over the stroke is 5,966 m/s², or 608 g. The ratio between them is 1.91, and the peak base force is 18,191 N. Structure on this round is sized against the peak at a safety factor of 2.0, because the peak is the load the round actually sees.
The peak cannot be tuned out of the system, and the arithmetic showing why is a single line. Peak base force occurs at x = 0, before the round has moved at all, so the acceleration is simply the pressure difference across the cup times the bore area over the mass: 30 bar less atmospheric, across 63.62 cm², into 1.6 kg. Accumulator volume sets exit velocity; it does not touch the peak. The only levers on launch shock are lower pressure, a smaller bore or a longer stroke, and a softer valve is not one of them.
This is the figure that decides what a nose is allowed to be. A solid steel slug does not care about 1,159 g. A payload does, and the arithmetic of what survives the stroke is the first page of the capture round's design at Encapsulator CS-111. It is also why the heavier class launches so much more gently: CS-120 peaks near 240 g, and live electronics can ride that.
From the muzzle the round is ballistic. The quadrant table below is computed as a point mass at ISA sea level with a drag coefficient of 0.35 on the Ø70 reference, and that assumption travels with the numbers.
Six fins are live from the first metre and the static margin holds the round on its axis, so the trajectory is set entirely at the mount: the launcher solves for azimuth and quadrant elevation, drives to it, and the arc follows. Nothing reaches the round after the muzzle and nothing aboard it corrects anything.
| Quadrant elevation | Range |
|---|---|
| 5° | 525 m |
| 10° | 894 m |
| 15° | 1,165 m |
| 20° | 1,364 m |
| 30° | 1,599 m |
| 45° | 1,636 m |
Range by quadrant elevation, computed as a point mass at ISA sea level with Cd0 = 0.35 taken on the Ø70 reference diameter. Cd0 is a literature value, and the table stands on it.
The round arrives with the energy the tube gave it, less what drag took on the way. Nothing else happens at the target, because there is nothing else aboard for anything else to happen with.
At 10° of quadrant elevation the round is doing 120.6 m/s at impact and carrying 11.7 kJ. At 45°, the long, high arc, it arrives at 99.7 m/s and 8.0 kJ. Both come off the same trajectory model and the same drag assumption.
Set those against the job. Structurally destroying a light composite or polymer airframe is an order-of-magnitude 0.1 to 1 kJ proposition. The round arrives with eight to twelve, and over-match at that scale is not a marginal call: it is one to two orders of magnitude of headroom against the airframes this class of threat is made of. So the engineering attention on this line goes where it belongs. Miss distance is the failure mode, not insufficient energy — and miss distance is a property of the cue, the laying solution and the mount, all of which live on the engagement and the launch platform rather than on the round.
A round that misses has nothing in it to initiate and no arming state to have got wrong, but it still lands with 7.3 to 16.8 kJ on the arc the laying solution set. The full muzzle arc and the ground downrange are an exclusion zone, kept clear while the launcher is armed and firing, as set out at safety on the launch line.
A steel, a glass-filled nylon, an elastomer or filled fluoropolymer for the sealing land, and a structural epoxy. The register is four lines long, and that is the point of it.
A short material register is a cheap round, a short supply chain and a forward cell that can make the airframe close to where it is used. Everything below is named as the reference the engineering works to.
| Ref | Where | Material | Properties as taken |
|---|---|---|---|
| M-01 | Nose slug | AISI 4140, normalized | UTS ~655 MPa · density 7,850 kg/m³ · reference ASTM A29/A331 · a mass item, not strength-critical |
| M-02 | Body, boom, fins, cup body | PA66-GF33, 33% glass-filled nylon 6/6 | 110 MPa and 7.0 GPa conditioned at 50% RH · density 1,400 kg/m³ · Poisson 0.35 · references ISO 1874 and UL 94 |
| M-03 | Obturating land | TPU 90A or filled PTFE | The sealing face against the bore |
| M-04 | Bonds | Two-part structural epoxy | Lap shear 20–30 MPa |
The round's material register. Standards are named as the references the engineering applies.
Read the register against the effect and the commercial argument follows from it. One steel slug does the work. One moulded polymer does the carrying, in four shapes off tooling the group owns. One land seals the bore. One adhesive holds it together. There is no initiator to store and no energetic material anywhere in the round or on the magazine that feeds it.
The round suits a buyer who has to hold ground against numbers and wants the exchange to run in their favour. It suits nobody looking for a missile, and it is not built to be mistaken for one.
The useful first conversation is about ground, numbers and authority. The figures above will still be here afterwards.
Bring the sector you have to hold, the ground you can stand a launch platform on, and the magazine depth the threat picture asks of you. Canadian Shield answers with the round, the tube and the interface between them. Enquiries are screened, counsel comes first on any international transfer, and permits are taken per shipment.
The rest of the line reads in order. CDNS UAV Platforms is the whole picture in one page. The launch platform is what throws the round. Heads and the nose interface is what goes on the front and what never crosses the joint. Guidance on this line puts the three tiers side by side. Safety on the launch line is the interlock chain and the exclusion zones. The engagement runs the loop from cue to reload.
All CDNS UAV Platforms designs are patent pending; international transfer is export-controlled and subject to Canadian government permits taken per shipment, and nothing on this page is an offer.
