The Virginia Spaceport at Wallops (east coast of USA, south from New York) advocates want to create a prize to foster use for the spaceport, and have floated an idea of a “one hour to Europe” style prize, the V Prize, but the rules aren’t yet finalized.
The requirements are quite tough. About 6000 km in one hour implies a speed of over Mach 6. There’s some discussion here too.
It’s probably a useless exercise but fun nevertheless, so I propose a notional atmospheric (as opposed to purely ballistic ICBM style) vehicle design for the prize.
First of all, out of the assumed 3600 seconds available from runway start to runway stop we reserve 600 seconds for takeoff, acceleration, deceleration and landing, and 3000 s for the 6000 km cruise. This means a cruise speed of 2 km/s, at an altitude of 10 to 20 km this means Mach 6.7.
We can ditch air breathing propulsion, it’s just too hard at such speeds as you’d have to use a scramjet, which is beyond the state of the art. Ramjets top out around Mach 5-6. These air breathers would also need a separate acceleration system.
We will also use a vehicle with wings, because that helps (we will see later). We won’t look at any of the massive literature because where would be the fun in that?
Now, we can examine the cruise problem with a few huge simplifications. We assume a constant lift to drag ratio, L/D, heretofore referred to as B. Now, at level flight, the lift equals the weight and thrust equals drag. Thus
That was easy! The virtual acceleration a is just like the gravity g in a normal hovering rocket, where, with a stationary vehicle you have gravity losses .
We can solve further:
Now, we can make the trajectory drop somewhat, to reduce the required delta vee. Delta vee from vertical is of course and thus total cruise delta vee is
This is simple, we accelerate to cruise velocity and altitude, delta vee is
Note that the vertical movement cancels out.
If we assume a very good lift to drag (remember this is hypersonic where the drag is a very large problem) of B=7, distance of 6E6 m distance, cruise velocity of 2E3 m/s, we get:
That kind of delta vee could perhaps be in the realm of possibility for a winged single stage.
Here’s a graph for different L/D ratios:
Ok, now we have some requirements. Let’s make a grand design. Take a SpaceX Falcon 1 and stick it on a delta wing platform. From the payload bay user’s guide:
Falcon 1 E first stage
- Empty mass 1.8 t
- Propellant 31 t
- Vacuum ISP 304 s
- We guesstimate sea level ISP 256 s
- Vacuum thrust 510 kN
- Sea level thrust 450 kN
- Length 27 m with interstage, upperstage and fairing. We estimate 17 m for the first stage alone.
- Material Aluminium
- Diameter 1.7 m
- Empty mass 8 t
- Falcon-derived “stage” mass (800 kg engine included) 2.8 t
- Wing, landing gear, control surface, cockpit mass of 5.2 t
- Landing gear is an aggressive 2% of total mass and thus 1.4 t
- Wings with stabilizers are 1 t a piece
- The rocket stage’s cradle is 0.5 t
- The front body and nose is 1 t
- The TPS for the wing leading edges and front is 0.8 t
- Propellant mass 62 t
- Total gross liftoff mass 70 t
- Thrust at sea level 440 kN yielding a T/W of 0.66
- Stage length 14 m
- Stage / fuselage diameter 2.4 m
- Nose length ~10 m
- Total fuselage length ~24 m
- Wingspan ~8 m (fuselage width + 1:7 Mach 7 hypersonic half triangle shape)
- Wing area 40 m^2 ?
Compare this to the delta-winged Mirage 2000:
- Length 14 m
- Wingspan 9 m
- Wing area 41 m^2
- Max takeoff mass 17 t
- Thrust 95 kN
- T/W 0.57
And F-106 Delta Dart:
- Length 22 m
- Wingspan 12 m
- Wing area 62 m^2
- Loaded mass 16 t
- Thrust 109 kN
The hypersonic plane would probably need deployable low speed canards for takeoff since the center of gravity would be so far forward. The wing and control surfaces could be quite separate from the monocoque aluminum main stage, minimizing heat transfer and easing construction. The heat load would mainly be from the front and underside and thus only affect the underbelly, nose cone, wing leading edge and vertical fins, which would all have high temperature materials. The landing gear could retract in the wing – main fuselage interface space.
Let’s call the design Slug.
It’s weird how the thing practically designed itself to turn out pretty much like X-24C-L301, a Lockheed design for a hypersonics testbed from the seventies. The dimensions are pretty similar, but the Lockheed plane used three propellants and very many different shaped tanks.
Lastly, I included a hasty sketch, comparing the cruiser to the few relevant craft. Scale should be mostly right:
This proposal is not serious but rather overoptimistic. I didn’t research background literature at all really, but it was fun to write nevertheless. The constant L/D of 7 at various speeds and angles of attack (with heavy mass at the start of the cruise you need more lift hence higher AoA) is where it already assumes the majority of the magic to happen. For example the L/D numbers for Concorde are: Low speed- 3.94, Approach- 4.35, 250 kn, 10,000 ft- 9.27, Mach 0.94- 11.47, Mach 2.04- 7.14. So the aerodynamics over a wide speed range seems like a very big challenge. Also the variable thrust and long duration of the burn probably require at least two propulsion systems, which was completely glossed over.
There’s a lot of material available on the net to examine stuff more closely, here’s one example of hypersonic shapes. Here’s NASA’s report about the design of X-24C, a 30 ton vehicle dropped from a B-52, having a payload of 2 t and providing 70 seconds of cruise at Mach 7.
Offer your criticisms. 🙂