It doesn't have reverse thrust and air-brakes, and relies purely on very strong wheel brakes. Wouldn't it be possible to rotate the canards by 90° (after touchdown) in order to create a very large air-brake? I don't think it would need too many modifications to the current form of the canards.
A number of things happen when you rotate the canards by 90°, and in no way I see how these could be addressed by
not too many modifications
Once you land, you need a certain amount of time to rotate the canards. During this time the canards will not produce a perfectly horizontal force, but it will have also a vertical component. Whether this component will be upwards or downwards it will depend on the rotation direction: rotate them with the leading edge up, and you will have some upward force; downward otherwise.
In both cases this is not ideal:
- an upward force will reduce the adherence of the nose wheel, reducing the steering authority
- a downward force will increase the load on the wheel, increasing the chance of tire burst and increasing the required size of the strut to sustain said load.
2. Deployed Status
Let's assume for a second that the transient problem can be avoided. Now you have two large surfaces perpendicular to the airflow that create a massive amount of drag. And torque.
You need then to design a structure that is capable of:
- keep the canard in place during the flight
- rotate the canard by 90°
- sustain the drag force during deceleration
- sustain the torque during deceleration
You can reduce the torque and drag forces to be transmitted through the mounting by delaying the deployment/rotation of the canards, but that would defeat the purpose or, at the very least, severely limit the usefulness of such a system.
In conclusion, a structure that would fulfill all the listed requirements is
- extremely likely to be heavier than equivalent brakes,
- more likely to be prone to structural problems due to complexity,
- more expensive due to maintenance,
making even less sense in an aviation application.
Would the stopping distance perhaps increase instead of decrease from using the canard as an air brake? My career involved stopping performance calculations for conventional airliners rather than delta wing configurations, but it seems that with existing landing technique you are getting a lot of drag benefit from the angle of attack of that big inefficient delta wing while the nose gear is still in the air. Maybe more drag than there is to be had from getting the nose on the ground relatively quickly so that a smallish canard can be rotated? To come out ahead, it might be necessary to have the canard air brake activate prior to nose gear touchdown. That would likely require automated real-time adjustment of the elevons to counteract the transitory moments, and perhaps a non-90 degree canard deployment angle during rollout to reduce the undesirable moment coming from a drag force well above the vertical CG.
Even if it happened to be the case that the canard was already capable of being rotated to any desired angle, given all of the above considerations something like slightly bigger drag chutes would presumably be a much easier way to get the same result.