By Tommy H. Thomason

Friday, December 16, 2011

A Brief History of Tailhook Design

I have been meaning to expand on my first discussion of the tailhook (HERE). The recent problems with the F-35C's brought that topic up to first on the list. More on that after a brief history of the tailhook.

The first landing of an airplane on a U.S. Navy ship, the cruiser Pennsylvania, was accomplished by a civilian pilot, Eugene Ely, on 18 January 1911—hence 2011 being the Centennial of Naval Aviation. A temporary wooden platform about 134 feet long and 32 feet wide had been added aft of the mainmast, extending aft over the after turret and past the stern of the ship. It angled upward from the fantail, the first 14-foot section at about a 30-degree angle and the remainder, less steeply but still "uphill" so as to help slow the airplane. Two low, wooden guide rails ran fore and aft on the platform about 12 feet apart to help keep the airplane on the deck. Two low canvas screens were strung across the deck about ten feet from its forward end and a high canvas screen was hung from the mast to the forward end of the platform. These foreshadowed the barriers and barricade respectively used on axial deck carriers to protect the crew forward and hopefully the pilot in the event that the airplane overran the landing area. Canvas was also slung outboard on both sides of the forward two thirds of the landing area to keep the airplane from falling into the sea if it came off the platform.

The arresting gear consisted of 22 pairs of 50-lb sandbags, each connected by a rope and placed outboard of the guide rails, which helped hold the rope above the deck. Each pair was three feet apart going up the deck. Three steel hooks were attached to the longitudinal frame of the landing gear of Ely's Curtiss pusher. These were intended to snag the ropes, with the bags then dragging the airplane to a stop. (The weight of each bag was carefully measured to insure that they were equal in order to reduce the likelihood of a bag having more drag than its partner and pulling the airplane to the side.)

The arresting system worked exactly as planned. The heritage of today's system is clearly evident.

It took a few more years of aircraft development before the U.S. Navy was ready to operate land planes from an actual aircraft carrier. The tailhook was instrumental to the success of the enterprise and a closely held innovation.

The first arresting-gear systems incorporated longitudinal wires as well as the cross-deck pendants. These were engaged by two-pronged hooks hanging down from the spreader bar between the main landing gear wheels. The purpose was to keep the airplanes from slewing off the deck or bouncing but they soon proved to be more trouble than they were worth and discarded.
A successful tailhook design was not as easy as it might seem.  The first requirement was structural: the attachment had to withstand a load two or three times greater than the weight of the airplane. Most installations were on the bottom of the aft fuselage, with the hook pivoting down from, in effect, the keel of the airplane ahead of the tail wheel.  This was mechanically and structurally simple, but meant that the retarding load of the hook ran below the aircraft center of gravity, causing the nose to pitch down during the arrestment to eliminate the resulting moment. This Grumman SF-1 tailhook is typical:
"Tail rise" with a low-mounted tailhook was a problem, as in this Bell Aircraft XFL-1 arrested landing, with the prop dangerously close to pecking the deck:

Grumman moved on to a "stinger" installation, in which the tailhook extended directly aft from the end of the tail fuselage. This was more complicated mechanically and structurally, but the retardation force was acting higher on the airframe, causing less of a pitch-down moment when the hook engaged a wire.

Vought originally utilized the stinger-type tailhook on its XF4U-1 Corsair but relocated it to the tail landing gear, still somewhat higher relative to the cg than the usual installation:
A beef up proved to be in order:

The Ryan FR-1 had a piston engine in the nose and a jet engine in the tail. Access to the jet engine was provided by removal of the aft fuselage. In order to avoid high loads on the attachment of the aft fuselage, the tail hook was attached forward  of that joint, probably as far forward as ever done.

Tail rise wasn't expected to be a problem because the airplane had a nose landing gear that protected the propeller. However, the length of the hook resulted in inflight engagements and its location, as would be expected, a nose-down pitching moment.
Loads on the nose wheel and landing gear attach structure proved to be excessive.

For more on the FR-1, en fran├žais,  see:

For its F5U, Vought designed a tailhook installation that was located above the "fuselage" (probably because one located on the belly would have resulted in excessive tail rise, although Vought engineers had a penchant for gadgetry).

 Grumman continued with the stinger tailhook through its F9F series. It continued to be satisfactory, although in one early test of the Panther, the arrestment pulled the removable aft fuselage off. This is a proof load test of the F9F-5 installation.
To simplify the installation, the Panther/Cougar hook was not retracted after landing but simply raised to the "stinger" position so the airplane could be taxied over the arresting wires, barriers, and barricade. It was then reloaded manually.

Grumman greatly simplified the mechanics and structure of the aft mounted hook in the F11F. It was stowed upside down and backwards so it simply dropped down from the extreme aft end of the fuselage.

After landing, the pilot raised it to the stinger position like the F9F's:
(The sailor was out there to pull the arresting cable off the hook if it did not fall off of its own accord.)

The F11F hook was double-jointed so it could be reloaded after the airplane had taxied forward and parked.This installation was innovative* but not imitated. For one thing, if when making a field landing the pilot decided after touchdown to drop the hook to engage the emergency arresting gear, it probably wouldn't rotate into position behind the aircraft.

Concerned with the nose-down pitching moment of even a stinger location of the tailhook for the F7U-1, Vought created a double-jointed installation in which the hook was attached at the top of the fuselage:
The design proved to be overly complicated and heavy (it also had a device that ejected the cross-deck pendant from the throat of the hook), so Vought reverted to a conventional belly mounting for the F7U-3. For more on the F7U-1 tail hook, click HERE.

Tail rise problems caused by low-hook attach points were dealt with by beefing up what broke, for example the F8U nose wheel.

In addition to structural and pitching moment concerns dealt with during predesign, the engineers also had to fine tune hook design and operation during development test and Navy evaluation. Hook damping was a cut and try process. Too little damping and the hook would skip, sometimes missing all the wires. Too much was hard on the aircraft structure, not to mention the deck. Hook length might also require experimentation in conjunction with damping changes. Too short a hook and long touchdowns risked missing all the wires; too long and an inflight engagement and overly hard landing might result. Trail angle was another; after problems were encountered in field and at-sea trials, the F4H tailhook operation was modified so that the trail angle decreased after main gear touchdown.

Which brings us to the F-35C. The first roll-in arrestment attempts at Lakehurst in early 2011 were disappointing to say the least: zero traps in eight tries. According to the recently published Quick Look Review of the Joint Strike Fighter Program:

"Root cause analysis identified three key AHS (Arresting Hook System) design issues: (1) the aircraft geometry has a relatively short distance between the aircraft’s main landing gear tires and tailhook point (when lowered), (2) tailhook point design was overemphasized for cable shredding (n.b. the tendency for the hook point to dig into and damage the cable) features versus ability to scoop low positioned cables, and (3) tailhook hold-down damper performance is ineffective to support damping of small bounces relative to runway/deck surface profiles."

This picture provides an approximation of the height of the hook above the deck relative to the main landing gear with the oleos fully extended with the F-35C at my guess at its angle of attack on approach. Note that the hook point is not below the wheels as it is on most other carrier-based airplanes and much closer to the wheels horizontally.

Contrast this hook-point position relative to the wheels both vertically and longitudinally with that of an F-18F Super Hornet's:
My guess is that the relative shortness of the hook is related to its closeness to the wheels, since an inflight engagement of a hook located so far forward relative to the wheels would generate a greater nose-down pitching moment than a hook located farther aft. Inflight engagement incidents would be minimized by having a short hook. However, the hook point's closeness to the wheels longitudinally appears to have resulted in an unanticipated problem that can be best understood by looking at this excellent summary of what happens when the wheels tramp down the arresting wire, also known as the cross-deck pendant:

Basically, the landing gear wheels mash down (trample is the term of art used in the report) the cross-deck pendant and it doesn't rebound high enough and quickly enough so that the current hook point (which was based on the proven F-18 design) can get under it. The proposed fixes are to revise the shape of the hook point and modify the damping of the hook so that it is less likely to skip over all the wires.
These changes will probably be sufficient so that more onerous changes to the hook installation are not required. (For a June 2014 update, see; the redesign was subsequently successfully qualified at sea). However, it once again illustrates the degree of difficulty in achieving the desired result on the first try and the necessity to plan time for redesign and retest of even the most basic and well known requirement.

* The reversed F11F tailhook was, however, not the first such installation. The Brits put a tailhook on an Airacobra I to evaluate arrestment of an airplane with a nose landing gear. It pivoted from a fitting just in front of the tail post and was manually stowed upside down and backwards. I'm not sure whether this unusual installation was because of the need to find a solid piece of structure to attach the hook to or to minimize the nose-down pitch on engagement. Maybe both. Captain Eric Brown made an unauthorized deck landing with it on Pretoria Castle on 4 April 1945 at the conclusion of a series of hook-up passes to evaluate flexible-deck approaches. By his own admission, he declared an emergency without cause in order to be get permission to land aboard and make the first landing of a tricycle aircraft on a British aircraft carrier. (The U.S. Navy had already done so, one of the few times that the Brits came in second on aircraft carrier milestones.)
The hook had to be relatively long because of the tricycle landing gear (see the FR-1 example above).


Logan Hartke said...

I recently caught some of the 1931 movie "Hell Divers" (by the famous "Spig" Wead) on TCM the other day and was reminded of this article. One of the aircraft catching the wire on the USS Saratoga had a pretty nasty case of tail rise which saw one prop blade hit the wooden deck, bending it back. If you haven't seen the movie, you need to do so. It has some fantastic footage of pre-war US Naval Aviation.

Anonymous said...

nice post, just a query about your pic showing the wheel to hook distance, I think there is parallax error, not a big point in the over all theme

Captain Hook said...

And the danger of putting all our eggs in one do it all superplane cutting edge basket.

Tailspin said...

I agree that the picture only provides an approximation of the relationship of the main gear and hook point, but in the Quick Look Review there is a table of wheel-to-hook distances for various Navy airplanes: the F-35C has the least by a considerable margin. It would also appear from the side view in the report that the F-35C just barely meets the requirement that the hook point be on the deck with the main gear shock struts at the normal static length and the nose gear strut compressed with a flat tire.

Anonymous said...

They meant "shredding". A problem with some earlier tailhook designs (A6/EA-6B for example) was a sharp hook point. This, in rare circumstances, would cause the hook point to split or part the arresting wire. Now when you look at a close up of a hook point the leading edges is almost rounded or smooth.

Tailspin said...

Ah, that shredding I understand. Thanks very much for the correction.

Avionic testing | AvionTEq said...

Thanks for sharing! I always enjoy reading any article related to aircraft history. So this is how tailhook design was formed, nice info!

Anonymous said...

Can anyone identify the tail shown on this web page?

Devona Grey said...

I'm trying to find out which metal between Aluminum, Titanium, and Steel would be best used for a tail hook in a Corsair Airplane. Which metals were used in the past?

Anonymous said...

I don't have your answer but one of the many factors which require consideration when specifying hook material is minimising abrasion of the hook surface by the arrester wire in the hook throat. The closer the hardness of the throat surface to that of the arrester wire the more satisfactory the situation for both hook and wire. Hooks cast from Cr/Mo alloys and hardened gave the best hook/wire interface.
Ref 'Farnborough and the Fleet Air Arm' by Geoffrey Cooper

So, food for thought when specifying a material.
Hope this small input helps?

Tailspin said...

Thanks for the input. The hook was generally steel. Note that the hook point itself was replaceable since it was a wear item.

JHoranLaw said...

Hook point and shaft are steel. Titanium and aluminum do not have a high enough ultimate yield strength for the loads generated. Titanium can be used in the keel beam but not on the arresting hook. The arresting hook connection to the keel beam probably has the highest loads on the aircraft.

Anonymous said...

I thought Hazen Pratt invented the tail hook