# Presentation: 000987

##  Micro Arcsecond Xray Imaging Mission: Pathfinder (MAXIM-PF)

**MAY 13th-17th, 2002**

** ****Micro Arcsecond Xray Imaging Mission: Pathfinder (MAXIM-PF)**

**Launch Vehicle Information**

- Final Version

## Launch Vehicle Options

**Projected Launch: Year: 2015**
**                       ****Mission Life 4 Years (5 Years Goal)     **
** ****LAI-MAXIM: S/C weight: X,XXX kg Dry Mass **
**                                  ****2,800 kg Wet Mass Approx. (Lift-off weight)**
**    **
** ****Earth escape C3 (km2/s2)= 0 / ****-.7**** / -2.2 / -2.7 **
**Launch Vehicle Case Study:**
**Ariane-5**
**Atlas V (521, 531, 441, 551)**
**Delta IV (4040, 4240, 4450, 4050H)**

## Launch Vehicle Options (Ariane V) 

**Ariane V (Fairings: 12.7m, 13.7m, 17m x 5.4m wide)**
**Launches: 7. Failures: 1. Success Rate: 85.71% pct. First Launch Date: 04 June 1996. Last Launch Date: 14 September 2000. **
**LEO Payload: ****16,000 kg****. to: 407 km Orbit. at: 51.6 degrees.**
**Payload: ****6,800 kg.**** to a: Geosynchronous transfer, 7 deg inclination**
**                               ****trajectory. Liftoff Thrust:**
**Payload: Escape Missions: To be demonstrated in the near future: Target orbit: V# 3 380m/s, Declination 1.99’, Cost Phase Duration 7000s, **
**Payload Performance: A5 ES ****3,500 kg**
**Launch Price $: 180.00 million. in 2000 price dollars.**
** **
**Stage Number: 0. 2 x Ariane 5-0 Gross Mass: 277,500 kg. Empty Mass: 39,800 kg. Thrust (vac): 660,000 kgf. Isp: 275 sec. Burn time: 129 sec. Isp(sl): 250 sec. Diameter: 3.0 m. Span: 3.0 m. Length: 31.6 m. Propellants: Solid No Engines: 1. P230 **
**Stage Number: 1. 1 x Ariane 5-1 Gross Mass: 170,800 kg. Empty Mass: 12,700 kg. Thrust (vac): 113,600 kgf. Isp: 430 sec. Burn time: 589 sec. Isp(sl): 340 sec. Diameter: 5.5 m. Span: 5.5 m. Length: 30.5 m. Propellants: Lox/LH2 No Engines: 1. Vulcain **
**Stage Number: 2. 1 x Ariane 5-2 Gross Mass: 12,500 kg. Empty Mass: 2,700 kg. Thrust (vac): 2,800 kgf. Isp: 324 sec. Burn time: 1,100 sec. Diameter: 4.0 m. Span: 5.5 m. Length: 3.4 m. Propellants: N2O4/MMH No Engines: 1. Aestus**
- Note: All prices are estimated in FY 2001 dollars based on current contracts or publicly disclosed information. Actual prices may vary
-           based on market conditions, competitive  negotiations and mission unique requirements. Figures do not include efforts to
-           support flying Dual Payload Configurations, major modification cost or Western Range Launches. Escalation figures for out
-           years  (2002-2003) are approximately 4% cumulative. For  budget planning purposes for AO/Future Studies.

## Launch Vehicle Options (Atlas V)

**Atlas V (521)**
**Performance: (C3 (km2/s2): 0:     4,545 kg Generic performance**
**                  ****(C3 (km2/s2): -.7:   4,605 kg Generic performance **
**                  ****(C3 (km2/s2): -2.2:  4,725 kg Generic performance**
**                  ****(C3 (km2/s2): -2.7:  4,765 kg Generic performance**
**Est. Cost (Fy’01) $112M std. Fairing**** **
**Atlas V (531)**
**Performance: (C3 (km2/s2): 0:     5,210 kg Generic performance**
**                  ****(C3 (km2/s2): -.7:   5,275 kg Generic performance **
**                  ****(C3 (km2/s2): -2.2:  5,420 kg Generic performance**
**                  ****(C3 (km2/s2): -2.7:  5.470 kg Generic performance**
**Est. Cost (Fy’01) $116M std. Fairing **
- Note: All prices are estimated in FY 2001 dollars based on current contracts or publicly disclosed information. Actual prices may vary
-           based on market conditions, competitive  negotiations and mission unique requirements. Figures do not include efforts to
-           support flying Dual Payload Configurations, major modification cost or Western Range Launches. Escalation figures for out
-           years  (2002-2003) are approximately 4% cumulative. For  budget planning purposes for AO/Future Studies.

## Launch Vehicle Options (Atlas V) 

**Atlas V (541)**
**Performance: (C3 (km2/s2): 0:     5,820 kg Generic performance**
**                  ****(C3 (km2/s2): -.7:   5,895 kg Generic performance **
**                  ****(C3 (km2/s2): -2.2:  6,055 kg Generic performance**
**                  ****(C3 (km2/s2): -2.7:  6,105 kg Generic performance**
**Est. Cost (Fy’01) $120M std. Fairing**** **
**Atlas V (551)**
**Performance: (C3 (km2/s2):   0:   6,330 kg Generic performance**
**                  ****(C3 (km2/s2): -0.7:  6,410 kg Generic performance **
**                  ****(C3 (km2/s2): -2.2:  6,585 kg Generic performance**
**                  ****(C3 (km2/s2): -2.7:  6,640 kg Generic performance**
**Est. Cost (Fy’01) $124M std. Fairing **
- Note: All prices are estimated in FY 2001 dollars based on current contracts or publicly disclosed information. Actual prices may vary
-           based on market conditions, competitive  negotiations and mission unique requirements. Figures do not include efforts to
-           support flying Dual Payload Configurations, major modification cost or Western Range Launches. Escalation figures for out
-           years  (2002-2003) are approximately 4% cumulative. For  budget planning purposes for AO/Future Studies.

##  Micro Arcsecond Xray  Imaging Mission: Pathfinder (MAXIM-PF)Atlas V (521) (531) (541) (551)

## Micro Arcsecond Xray Imaging Mission: Pathfinder (MAXIM-PF)Atlas V (521) (531)

- Assumptions:
-  Atlas V (521)
-  - 3-sigma mission required margin, plus additional reserves as determined by the LSP.
-  - Launch from SLC-41 at CCAFS (Cape Canaveral Air Force Station).
-  - Performance values assume harness, logo, reradiating antenna, 3 payload fairing doors.
-  - Payload mass greater than 9000 kg may require mission unique accommodations.
-  - Type B2 payload adapter plus type C2 spacer.
-  - 5-meter Short Payload Fairing.
-  - 185 km (100 nmi) minimum park orbit perigee altitude.
-  - 185 km (100 nmi) minimum escape orbit perigee altitude.
-  - Performance shown is applicable for declinations between 28.5 deg. and –28.5 deg.
-  Last Updated: 7/3/01 4:34:09 PM
-  Atlas V (531)
-  - 3-sigma mission required margin, plus additional reserves as determined by the LSP.
-  - Launch from SLC-41 at CCAFS (Cape Canaveral Air Force Station).
-  - Performance values assume harness, logo, reradiating antenna, 3 payload fairing doors.
-  - Payload mass greater than 9000 kg may require mission unique accommodations.
-  - Type B2 payload adapter plus type C2 spacer.
-  - 5-meter Short Payload Fairing.
-  - 185 km (100 nmi) minimum park orbit perigee altitude.
-  - 185 km (100 nmi) minimum escape orbit perigee altitude.
-  - Performance shown is applicable for declinations between 28.5 deg. and –28.5 deg.
-  Last Updated: 7/3/01 4:34:24 PM

## Micro Arcsecond Xray Imaging Mission: Pathfinder (MAXIM-PF)Atlas V (541) (551)

- Assumptions:
-  Atlas V (541)
-  - 3-sigma mission required margin, plus additional reserves as determined by the LSP.
-  - Launch from SLC-41 at CCAFS (Cape Canaveral Air Force Station).
-  - Performance values assume harness, logo, reradiating antenna, 3 payload fairing doors.
-  - Payload mass greater than 9000 kg may require mission unique accommodations.
-  - Type B2 payload adapter plus type C2 spacer.
-  - 5-meter Short Payload Fairing.
-  - 185 km (100 nmi) minimum park orbit perigee altitude.
-  - 185 km (100 nmi) minimum escape orbit perigee altitude.
-  - Performance shown is applicable for declinations between 28.5 deg. and –28.5 deg.
-  Last Updated: 7/3/01 4:34:39 PM
-  Atlas V (551)
-  - 3-sigma mission required margin, plus additional reserves as determined by the LSP.
-  - Launch from SLC-41 at CCAFS (Cape Canaveral Air Force Station).
-  - Performance values assume harness, logo, reradiating antenna, 3 payload fairing doors.
-  - Payload mass greater than 9000 kg may require mission unique accommodations.
-  - Type B2 payload adapter plus type C2 spacer.
-  - 5-meter Short Payload Fairing.
-  - 185 km (100 nmi) minimum park orbit perigee altitude.
-  - 185 km (100 nmi) minimum escape orbit perigee altitude.
-  - Performance shown is applicable for declinations between 28.5 deg. and –28.5 deg.
-  Last Updated: 7/3/01 4:34:56 PM

## Launch Vehicle Options (Delta IV) (4040-12)(4240-12)

**Delta IV (4040-12)**
**Performance: (C3 (km2/s2): 0:     2,735 kg Generic performance**
**                  ****(C3 (km2/s2): -.7:   2,780 kg Generic performance **
**                  ****(C3 (km2/s2): -2.2:  2,880 kg Generic performance**
**                  ****(C3 (km2/s2): -2.7:  2,915 kg Generic performance**
**Est. Cost (Fy’01) $87M std. Fairing (4m Fairing std./ 5m Fairing NA)**
**Delta IV (4240-12)**
**Performance: (C3 (km2/s2): 0:     4,075 kg Generic performance**
**                  ****(C3 (km2/s2): -.7:   4,135 kg Generic performance **
**                  ****(C3 (km2/s2): -2.2:  4,265 kg Generic performance**
**                  ****(C3 (km2/s2): -2.7:  4,310 kg Generic performance**
**Est. Cost (Fy’01) $97M std. Fairing (5m Diameter)**
- Note: All prices are estimated in FY 2001 dollars based on current contracts or publicly disclosed information. Actual prices may vary
-           based on market conditions, competitive  negotiations and mission unique requirements. Figures do not include efforts to
-           support flying Dual Payload Configurations, major modification cost or Western Range Launches. Escalation figures for out
-           years  (2002-2003) are approximately 4% cumulative. For  budget planning purposes for AO/Future Studies.

## Launch Vehicle OptionsDelta IV (4450-14) (4250H-19)

**Delta IV (4450-14)**
**Performance: (C3 (km2/s2): 0:     4,580 kg Generic performance**
**                  ****(C3 (km2/s2): -.7:   4,650 kg Generic performance **
**                  ****(C3 (km2/s2): -2.2:  4,795 kg Generic performance**
**                  ****(C3 (km2/s2): -2.7:  4,845 kg Generic performance**
**Est. Cost (Fy’01) $107M std. Fairing (5 Meter Diameter)**
**Delta IV (4250H-19)**
**Performance: (C3 (km2/s2): 0:     9,305 kg Generic performance**
**                  ****(C3 (km2/s2): -.7:   9,410 kg Generic performance **
**                  ****(C3 (km2/s2): -2.2:  9,645 kg Generic performance**
**                  ****(C3 (km2/s2): -2.7:  9,725 kg Generic performance**
**Est. Cost (Fy’01) $150-160M std. Fairing (5 Meter Diameter)**
- Note: All prices are estimated in FY 2001 dollars based on current contracts or publicly disclosed information. Actual prices may vary
-           based on market conditions, competitive  negotiations and mission unique requirements. Figures do not include efforts to
-           support flying Dual Payload Configurations, major modification cost or Western Range Launches. Escalation figures for out
-           years  (2002-2003) are approximately 4% cumulative. For  budget planning purposes for AO/Future Studies.

## Launch Vehicle: Baseline Delta IV (4040-12)

**Launch Vehicle: ****Baseline ****Delta IV (4040-12)**

- Delta IV (4040-12)
- Performance: (C3 (km2/s2): 0:     2,735 kg Generic performance
-                   (C3 (km2/s2): -.7:   2,780 kg Generic performance
-                   (C3 (km2/s2): -2.2:  2,880 kg Generic performance
-                   (C3 (km2/s2): -2.7:  2,915 kg Generic performance
- Est. Cost (Fy’01) $87M std. Fairing (4m Fairing std. / 5m Fairing NA)
- Note: All prices are estimated in FY 2001 dollars based on current contracts or publicly disclosed information. Actual prices may  vary based on market conditions, competitive  negotiations and mission unique requirements. Figures do not include efforts to support flying Dual Payload Configurations, major modification cost or Western Range Launches. Escalation figures for out years  (2002-2003) are approximately 4% cumulative. For  budget planning purposes for AO/Future Studies.

- 7

## Launch Vehicle: Baseline Delta IV (4240-12)

**Launch Vehicle: ****Baseline ****Delta IV (4240-12)**

- Delta IV (4240-12)
- Performance: (C3 (km2/s2): 0:     4,075 kg Generic performance
-                          (C3 (km2/s2): -.7:   4,135 kg Generic performance
-                          (C3 (km2/s2): -2.2:  4,265 kg Generic performance
-                         (C3 (km2/s2): -2.7:  4,310 kg Generic performance
- Est. Cost (Fy’01) $97M std. Fairing (5m Diameter)
- Note: All prices are estimated in FY 2001 dollars based on current contracts or publicly disclosed information. Actual prices may
-               vary based on market conditions, competitive  negotiations and mission unique requirements. Figures do not include efforts
-                 to support flying Dual Payload Configurations, major modification cost or Western Range Launches. Escalation figures for out years  (2002-2003) are approximately 4% cumulative. For  budget planning purposes for AO/Future Studies.

- 7

## Launch Vehicle: Baseline Delta IV (4450-14)

**Launch Vehicle: ****Baseline ****Delta IV (4450-14)**

- Delta IV (4450-14)
- Performance: (C3 (km2/s2): 0:     4,580 kg Generic performance
-                          (C3 (km2/s2): -.7:   4,650 kg Generic performance
-                          (C3 (km2/s2): -2.2:  4,795 kg Generic performance
-                          (C3 (km2/s2): -2.7:  4,845 kg Generic performance
- Est. Cost (Fy’01) $107M std. Fairing (5 Meter Diameter)
-  Note: All prices are estimated in FY 2001 dollars based on current contracts or publicly disclosed information. Actual prices may vary based on market conditions, competitive  negotiations and mission unique requirements. Figures do not include efforts to       support flying Dual Payload Configurations, major modification cost or Western Range Launches. Escalation figures for out
-      years  (2002-2003) are approximately 4% cumulative. For  budget planning purposes for AO/Future Studies.

- 7

##  MAXIM Pathfinder (LAI-MAXIM) Delta VI: (4040-12,4240-12,4450-14,4050H-19

## MAXIM Pathfinder (LAI-MAXIM) Delta VI: (4040-12,4240-12)

- Assumptions:
-  Delta IV (4040-12)
-  - 3-sigma probability of Stage 2 commanded shutdown, plus additional reserves as determined by the LSP.
-  - 1194-4 payload adapter.
-  - Launch from SLC-37 at CCAFS (Cape Canaveral Air Force Station).
-  - 185 km (100 nmi) circular park orbit at 28.9 deg. inclination.
-  - 185 km (100 nmi) escape orbit perigee.
-  - Performance shown is applicable for declinations between 28.9 deg. and –28.9 deg.
-  Last Updated: 7/3/01 4:30:12 PM
-  Delta IV (4240-12)
-  - 3-sigma probability of Stage 2 commanded shutdown, plus additional reserves as determined by the LSP.
-  - 1194-4 payload adapter.
-  - Launch from SLC-37 at CCAFS (Cape Canaveral Air Force Station).
-  - 185 km (100 nmi) circular park orbit at 28.9 deg. inclination.
-  - 185 km (100 nmi) escape orbit perigee.
-  - Performance shown is applicable for declinations between 28.9 deg. and –28.9 deg.
-  Last Updated: 7/3/01 4:30:49 PM

## MAXIM Pathfinder (LAI-MAXIM) Delta VI: (4450-14,4050H-19)

- Assumptions:
- Delta IV (4450-14)
-  - 3-sigma probability of Stage 2 commanded shutdown, plus additional reserves as determined by the LSP.
-  - 1194-5 payload adapter.
-  - Launch from SLC-37 at CCAFS (Cape Canaveral Air Force Station).
-  - 185 km (100 nmi) circular park orbit at 28.9 deg. inclination.
-  - 185 km (100 nmi) escape orbit perigee.
-  - Performance shown is applicable for declinations between 28.9 deg. and –28.9 deg.
-  Last Updated: 7/3/01 4:31:05 PM
-  Delta IV (4050H-19)
-  - 3-sigma probability of Stage 2 commanded shutdown, plus additional reserves as determined by the LSP.
-  - 1194-5 payload adapter.
-  - Launch from SLC-37 at CCAFS (Cape Canaveral Air Force Station).
-  - 185 km (100 nmi) circular park orbit at 28.9 deg. inclination.
-  - 185 km (100 nmi) escape orbit perigee.
-  - Performance shown is applicable for declinations between 28.9 deg. and –28.9 deg.
-  Last Updated: 7/3/01 4:31:20 PM