# Presentation: 341663

## Micro Arcsecond X-ray Imaging MissionPathfinder (MAXIM-PF)

**Mechanical**
**George Roach**
**Dave Peters**
**17 May 2002**

- “Technological progress is like an axe in the hands of a pathological criminal” 	Albert Einstein

## Design Mission Unique spacecraft bus
HUB spacecraft consists of one Core S/C and 6 Petal S/C. These petal S/C will eventually become free flyer S/C.
Core S/C and Petal S/C are structurally the same.
A Detector spacecraft will attached to the HUB spacecraft then separate on orbit.

Accommodate a orbit Transfer Module (propulsion). 

For payload accommodation use:
Use standard, highly successful mechanical designs with heritage, I.e. fixtures, bracket and fittings where possibly.  
Minimize complex procedures.

Baseline Delta IV –5m x 14.3m launch vehicle shroud

- HUB spacecraft consists of one Core S/C and 6 Petal S/C. These petal S/C will eventually become free flyer S/C.
- Core S/C and Petal S/C are structurally the same.
- A Detector spacecraft will attached to the HUB spacecraft then separate on orbit.
**Accommodate a orbit Transfer Module (propulsion). **
** **
**For payload accommodation use:**
- Use standard, highly successful mechanical designs with heritage, I.e. fixtures, bracket and fittings where possibly.
- Minimize complex procedures.
**Baseline Delta IV –5m x 14.3m launch vehicle shroud**

**Overview **

## Launch Configuration

**Launch Configuration**

- Delta IV Heavy
- 5m X 19.1m fairing

**Delta IV**
**5m X 14.3m fairing**

- P/L Sta. 0.00

- Sta. 1550

- C.G. Sta. 2500

- Sta. 4300

- Sta. 7600

- Propulsion/Hub SpaceCraft

- Hub SpaceCraft/Detector SpaceCraft

- Propulsion/Hub SpaceCraft

**Delta IV**
**5m X 14.3m fairing**

## Mission Sequence

- Launch

- Transfer Stage

- Science Phase #1
- Low Resolution

- 200 km

- Science Phase #2
- High Resolution

- 1 km

- 20,000 km

## Component LayoutHub Core & Petal

- Hub Core

- Hub Petal (6)

- LOS Laser

- Detector S/C
- Payload Adapter Fitting

- Optical Module (9)

- Optical Module (11)

- Comm Antenna
- (S/C to S/C  0.3 m)

## Component LayoutDetector

**Component Layout****Detector**

- Solar Array (4.5 m2)

- Comm Antenna
- (Ground/SpaceCraft 0.5 m)

- Comm Antenna
- (S/C to S/C  0.3 m)

- Comm Antenna
- (Ground/SpaceCraft 0.5 m)

- LOS laser receiver

- CCD Camera

- CCD Electronics

- Thermal Shade (2.3 m2)

## Structure Mass

**Structure Mass**
- Hub Core – 57 kg
- Hub Petal – 56 kg
- Detector Payload Adapter Fitting –  12 kg
- Detector – 85 kg

## No spacecraft clearance issues
Ample clearance inside the launch vehicle fairing for all spacecraft appendages
Ample volume for spacecraft subsystems inside the bus
Mechanical interfaces:
Mission axial C.G. height within limits for launch vehicle PAF
Mission lateral C.G. are within limits for launch vehicle PAF
Mission stiffness for launch vehicle is TBD at this phase of the study
The concept of latching / unlatching the Freeflyer spacecraft has not been looked into for this phase of the study. However the concept has been used successfully many times in the past. One example is the MultiMission Spacecraft concept used for several satellites including, Solar Maximum, UARS, and EUVE. It has also been adapted for use on some Hubble components.
The actual spacecraft subsystems are not shown due to the time element.  The spacecraft density is low enough to accommodate these volumes. 

- Ample clearance inside the launch vehicle fairing for all spacecraft appendages
**Ample volume for spacecraft subsystems inside the bus**
**Mechanical interfaces:**
- Mission axial C.G. height within limits for launch vehicle PAF
- Mission lateral C.G. are within limits for launch vehicle PAF
- Mission stiffness for launch vehicle is _**TBD**_ at this phase of the study
**The concept of latching / unlatching the Freeflyer spacecraft has not been looked into for this phase of the study. However the concept has been used successfully many times in the past. One example is the MultiMission Spacecraft concept used for several satellites including, Solar Maximum, UARS, and EUVE. It has also been adapted for use on some Hubble components.**
**The actual spacecraft subsystems are not shown due to the time element.  The spacecraft density is low enough to accommodate these volumes. **

** ****Issues and Concerns**

## MECHANICAL

**  ****BACK-UP SLIDES**

## Launch Vehicle Capabilities

## Spacecraft Bus Densities 

**Spacecraft Bus Densities **

## OPTIC HUB to FREE FLYERLatching Concept (example)

- This picture shows the latching / unlatching of Multi-Mission Modular Spacecraft.  This basic
- concept could be used for the LAI-MAXIN “OPTIC HUB” to “FREE FLYER” configuration

**Free Flyer (s)**
**Spacecraft**

**Optic Hub**
**Spacecraft**

## DELTA IV- 1666-4 PAF C.G. 

**DELTA IV- 1666-4 PAF C.G. **

- 3264 kg

- 2500 mm

## Detector Mass Propertiesand Area’s

**Detector Mass Properties****and Area’s**

- 3.3^2m

- 1.9^2m

- 5.6^2m

- Y

- Z

- X