Presentation is loading. Please wait.

Presentation is loading. Please wait.

ADAPTING MARS ENTRY, DESCENT AND LANDING SYSTEM FOR EARTH J. Heilimo* (1), S. Aleksashkin (2), A.-M. Harri (1), H. Guerrero (4), V. Koryanov (3), H. Haukka.

Similar presentations


Presentation on theme: "ADAPTING MARS ENTRY, DESCENT AND LANDING SYSTEM FOR EARTH J. Heilimo* (1), S. Aleksashkin (2), A.-M. Harri (1), H. Guerrero (4), V. Koryanov (3), H. Haukka."— Presentation transcript:

1 ADAPTING MARS ENTRY, DESCENT AND LANDING SYSTEM FOR EARTH J. Heilimo* (1), S. Aleksashkin (2), A.-M. Harri (1), H. Guerrero (4), V. Koryanov (3), H. Haukka (1), W. Schmidt (1), T. Siili (1), V. Finchenko (2), M. Martynov (2), B. Ostresko (2), A. Ponomarenko (2), V. Kazakovtsev (3), S. Martin (4), 1

2 RITD Project team 2 Institutio Nacional de Técnica Aerospacial Bauman Moscow State Technical University Lavochkin Association (1) (2) (3) (4)

3 RITD Project scope Mars MetNet Landers (MML) Semihard landing to Mars Two phase Inflatable EDLS Can the same EDLS be used for Earth entry? Stability during transsonic phase? Scaling and modifications required? 3

4 4 Main Parameters of MML

5 MetNet descent vehicle structure 5 MIBD Aerodynamic shield (AS) AS body MIBD inflation system MIBD DV body Movable cone Movable cone drive AIBD MIB D Shock absorber Cover Payload container

6 6 Rigid TPC: Sublimating radiolucent material. Sublimation temperature T=600 ⁰ С Rigid TPC: Sublimating radiolucent material. Sublimation temperature T=600 ⁰ С Flexible TPC : Thermal protection jacket two layers of MLI fabric (Т<1200 ⁰ С), sublimating material Flexible TPC : Thermal protection jacket two layers of MLI fabric (Т<1200 ⁰ С), sublimating material Flexible TPC : Heat-insulating mat – MLI Sublimating material on outer surface of the mat (T<600 ⁰ С) Flexible TPC : Heat-insulating mat – MLI Sublimating material on outer surface of the mat (T<600 ⁰ С)

7  Minimum deformation of MIBD shape;  Thermal and mechanical loads to DV structure shall within limits;  Descent Vehicle dynamic stability during descent.  Minimum deformation of MIBD shape;  Thermal and mechanical loads to DV structure shall within limits;  Descent Vehicle dynamic stability during descent.  Atmospheric density and composition;  Re-entry velocity - Ventry;  Angle of re-entry - θentry.  Atmospheric density and composition;  Re-entry velocity - Ventry;  Angle of re-entry - θentry.  level of specific heat flux to MetNet DV mockup surface;  value of specific quantity of heat falling to MetNet DV mockup surface;  value of MetNet DV mockup thermal protection ablation.  level of specific heat flux to MetNet DV mockup surface;  value of specific quantity of heat falling to MetNet DV mockup surface;  value of MetNet DV mockup thermal protection ablation. 7 Aim: study of feasibility of MetNet DV entry into the Earth atmosphere. Factors affecting DV atmospheric motion: Parameters of thermal loading simulation: Criteria:

8 Conclusions 8 V entry θ entry V entry θ entry Analysis of conditions of DV entry into the Earth atmosphere, meeting thermal loading design parameters Estimation of the trajectory of DV motion in the Earth atmosphere Analysis of DV motion dynamics with regard to the center of gravity

9 V entry = 5250 m/s θ entry =-3 deg. V entry = 5250 m/s θ entry =-3 deg. 9 Results of analysis of 120 variants of trajectories Table of correspondence of thermal parameters at DV descending in the Earth and Mars atmospheres

10 10 Mars (  entry = – 9.49  ; V entry = 4586 m/s) The Earth (  entry = – 3.00  ; V entry = 5250 m/s) q, kW/m 2 t, s

11 11 Mars (  entry = – 9.49  ; V entry = 4586 m/s) The Earth (  entry = – 3.00  ; V entry = 5250 m/s) t, s ∆δ, mm Linear ablation of sublimating material along the trajectory of descent

12 T, ˚C The Earth (  entry = – 3.00  ; V entry = 5250 m/s) 12 Mars (  entry = – 9.49  ; V entry = 4586 m/s) black curve – outer surface of TPC red curve – PLC cover black curve – outer surface of TPC red curve – PLC cover Dynamics of DV PLC cover temperature condition along the trajectory of descent t, s

13 Mars The Earth 13 Time, s Altitude, m Descent trajectory

14 Mars The Earth 14 Velocity variation along the trajectory of descent Time, s Velocity, m / s

15 Mars The Earth 15 Dynamic pressure variation during the descent Time, s Dynamic pressure, Pa

16 Mars The Earth 16 Axial g-load variation during the descent Time, s G-load, unit

17 17 Inflation System Variant 1 Inflation System Variant 1 Pyrotechnic Gas Generator (PGG) PGG... 5 items Mass – 2.5 kg Inflation System Variant 2 Inflation System Variant 2 PGG Gas tank Gas tank Pyrovalve and hoses Mass – 1.5 kg

18 18 Variation of spatial angle of attack vs. time Variation of transverse angle rates

19 19  Entry conditions V entry = 5250 m/s, θ entry = -3 deg are feasibile for MetNet DV descend and landing to the Earth atmospere.  TPC ablation and thermal protection temperature conditions are comparable.  At stabilization of DV by spinning and oriented entry into the Earth atmosphere the MetNet DV preserves stability along the whole path. Angular motion characteristics are preserved.  The mechanical loads to MIBD due dynamic pressure interaction practically coincide.  In Earth conditions, due to more dense atmosphere at altitudes below 12 km, staged pressurization of AIBD is required. The pressurization system will increase DV mass by kg (depending of chosen variant).


Download ppt "ADAPTING MARS ENTRY, DESCENT AND LANDING SYSTEM FOR EARTH J. Heilimo* (1), S. Aleksashkin (2), A.-M. Harri (1), H. Guerrero (4), V. Koryanov (3), H. Haukka."

Similar presentations


Ads by Google