Team PM8 Eventus Slide 1

Commercial spaceflight has seen increased activity as more privately owned companies invest in the venture. To avoid a catastrophic accident that may lead to a loss of human life, the team has been given a request for proposal by NASA to create an emergency crew rescue vehicle, or ECRV, capable of rescuing a crew from a vehicle in distress, VID. The ECRV must be able to: Support launch on short notice from a United States Air Force Base Rescue the stranded civilians from any orbital inclination between the altitudes of 200 and 1000 km Perform atmospheric re-entry, and Utilize powered flight back to the launch site Project Overview [1] Slide 2

To size the two stage launch vehicle, prior art was examined to obtain a design basis To size the two stage launch vehicle, prior art was examined to obtain a design basis Requirements: 30,000kg to LEO, Minimal 6m core diameter for payload Requirements: 30,000kg to LEO, Minimal 6m core diameter for payload Several theoretical and existing launch platforms examined, NASA’s Saturn C-3 was chosen to be basis of the design Several theoretical and existing launch platforms examined, NASA’s Saturn C-3 was chosen to be basis of the design Launch Vehicle Design Launch VehiclePayload to LEO (kg)Core Diameter (m)Total Mass (kg) Space Shuttle24, ,029,633 Energia88, ,524,600 Falcon Heavy53, ,462,836 Delta IV Heavy25, ,400 Saturn C-336, ,023,670 [2,3,4,5,6,7,8,9] Slide 3

Launch vehicle stages were massed using the ideal ΔV split Launch vehicle stages were massed using the ideal ΔV split First stage: 982,017 kg, 39.7% of ΔV First stage: 982,017 kg, 39.7% of ΔV 2 F-1 Engines 2 F-1 Engines Second stage: 196,128 kg, 60.3% of ΔV Second stage: 196,128 kg, 60.3% of ΔV 4 J-2 Engines 4 J-2 Engines Total Mass (including payload): 1,205,305.8 kg Total Mass (including payload): 1,205,305.8 kg Launch Vehicle Specifications Slide 4

ECRV Capsule Design [10] [11] Falcon HeavyFregat Propellant Mass90,000 kg5,350 kg Inert Mass4,900 kg1,150 kg Inert Mass Fraction Engine ISP340 s327 s Payload Capacity53,000 kg13,740 kg [11, 12] Slide 5

Power Plant and Heat Shield [13] Power Plant Merlin 1-D vac engine I SP = 340 – 342 s Thrust = 501 kN [14] Heat Shield [16] [15] Slide 6 AVCOAT ablative heat shield Density: 512 kg/m^3 Thickness: 16.93cm [17,18]

Mass of ECRV Third Stage Used: Used: Falcon I SP and f inert values Falcon I SP and f inert values m pay = 9060 kg (mass of aircraft) m pay = 9060 kg (mass of aircraft) m heat shield = (Density)(Thickness)(Surface Area) m heat shield = (Density)(Thickness)(Surface Area) Total Mass of Third Stage = Total Mass of Third Stage = 27, kg Slide 7

Aerotrek A220 Aircraft Design Volvo XC90 McDonnell Douglas DC-10 Cessna Citation Mustang Cessna Citation X [19] [20] [21] [22] [23] Slide 8

Aircraft Design Slide 9

Aircraft Design Slide 10

At ejection, C L = 0.89, C D = 0.05 and T R = 5.59 kN. At ejection, C L = 0.89, C D = 0.05 and T R = 5.59 kN. This value for C L g at ejection means that the aircraft must fly at an angle of attack of 7-8 degrees to maintain steady and level flight. This value for C L g at ejection means that the aircraft must fly at an angle of attack of 7-8 degrees to maintain steady and level flight. The value for T R is much lower than the T A at ejection. The value for T R is much lower than the T A at ejection. To ensure than C L never reaches C L,Max the plot of C L versus altitude is discussed in the coming slides. To ensure than C L never reaches C L,Max the plot of C L versus altitude is discussed in the coming slides. Also, to ensure that T R never exceeds T A throughout the course of flight, the behavior of T R is explored with respect to altitude. Also, to ensure that T R never exceeds T A throughout the course of flight, the behavior of T R is explored with respect to altitude. Aircraft Performance Slide 11

C L VS. Altitude Slide 12

Thrust Required VS. Altitude Slide 13

Emergency Scenarios and Glide Range Emergency scenarios need to be assessed. For example, engine failure and running out of fuel mid-flight Glide range is studied to analyze the capabilities of the aircraft Glide range is maximized at 9000 meters at a value of 140 km This determines the cruise altitude since this altitude is the safest in a time of emergency. Slide 14

Range and Choices for Cruise Velocity Slide 15

Rate of Climb and Service Ceiling Slide 16

Mass Estimation [24,25,26,27,28] Fuel tank mass is negligible Passenger Mass Space suits Life Support System Aluminum Oxygen Tanks Valves with Pressure Gauge Portable Oxygen System Landing Gear 6-10% of the aircraft mass Chose 8% of the aircraft mass Slide 17

Material Breakout of Eventus Similar Materials Used As Boeing Lightweight New technology Carbon Fiber Higher Strength Lighter Mass Stiffer [29,30] Slide 18

Mission Design Slide 19

Andersen Air Force Base Validation Mean ΔV effective at Andersen AFB: km/s Mean ΔV effective at Hickam AFB: km/s Mean ΔV effective at Kadena AB: km/s Worst Case Scenario ΔV effective at Andersen AFB: km/s [31,32,33,34,35] Slide 20

Mission Design Launch To LEO Slide 21 Minimum initial mass of Eventus: 1,205,305.8 kg Accompanying Stage 1 ΔV fraction: [2,8,9]

Plane Change (if required) Move From checkout orbit inclination to VID orbital inclination Hohmann To VID Two Burn Hohmann to enter same orbit as VID Rendezvous Dock with VID Plane Change (if required) Perform plane change to enter at inclination within range of aircraft Deorbiting Maneuver Single burn transfer place Mission Design Post LEO ManeuverMaximum ValueΔVΔV Plane Change To VID inclination13.58°1.8 km/s Hohmann to VID800 km0.2 km/s Plane Change For Range18.86°2.5 km/s Deorbiting Manuver1000 km0.3 km/s Slide 22 Total ΔV = 3 km/s

Slide 23 Mission Design Post Re-Entry, Powered Flight and Landing

Cost Analysis Total cost of Eventus: $141,165, Slide 24 [36]

Any Questions?

http ://mobile.ztopics.com/Merlin%20(rocket%20engine)/ http :// “ DVJ2PF4SWyASmkIHQDA References Slide 25