Let's calculate it then using the rocket equation and see who's right.
Δv=ve*ln(m0/mt)
ve=Isp*g0
Δv= Isp*g0*ln(m0/mt)
Δv= Difference in velocity.
ve= Effective exhaust velocity
Isp=Specific Impulse in seconds
g0=gravity
m0= Initial mass (launch weight)
mt= Final Mass (weight without fuel)
Propellant Mass Fraction= 1- (m0/mt)
The specific impulse of a modern composite solid fuel is around 260s ( TABLE 1
https://www.jhuapl.edu/Content/techdigest/pdf/V04-N03/04-03-Billig.pdf )
The initial mass of next-generation Bora is 2500kg
The final mass of next-generation Bora is 800kg
The propellant mass fraction is 0.68 which is on the "low" side. That can be improved even more. (It means %68 of the rocket's total weight is fuel)
https://www.omnicalculator.com/physics/delta-v when we calculate it from here we found a delta-v of ~2.9 km/s (10440 km/h)
This is enough delta-v to reach 900+km.
BTW PrsM currently uses the existing 227kg WDU-18/B unitary high-explosive warhead. A New 200-pound warhead is in development for the 1000+km multi-mode seeker version. There are also plans to make it compatible with the existing or newly developed cluster munition warheads.
Real-life telemetry data of a 1000km ballistic missile.
View attachment 44331