Nuclear Thermal Propulsion (NTP): A Proven, Growth Technology for 'Fast Transit' Human Missions to Mars

Probably not a substantial claim: may not pass S3 (load-bearing), S4 (based).

For the longer in-line tank, the cryocooler system requires about 9.13 kWe of electrical power supplied by PVAs on the NTPS and in-line tank.

“For the longer in-line tank, the cryocooler system requires ~9.13 kW e of electrical power supplied by PVAs on the NTPS and in-line tank.”

May combine two claims.

The 130-day Copernicus-2 mission uses four primary burns with three restarts and about 253.8 t of LH2 propellant.

“For this 130-day transit mission, there are four primary burns (with three restarts) and ~253.8 t of LH 2 propellant is used.”

May combine two claims.

The Copernicus crewed MTV is about 93.7 m long and has an IMLEO of about 331.7 t for the 150-day transit 2033 mission.

“The Copernicus crewed MTV has an overall length of ~93.7 m (Fig. 7) and an IMLEO of ~331.7 t for the 150-day transit 2033 mission.”

May combine two claims.

Copernicus-2 requires one additional HLV launch and development of an in-line tank element with its own ZBO cryocooler system.

“Copernicus-2 also requires one additional HLV launch as well as the development of the in-line tank element with its own ZBO cryocooler system.”

May combine two claims.

The round-trip mission has four primary burns with three restarts and uses about 168.7 t of LH2 propellant.

“For the round trip mission, there are four primary burns (three restarts) that use ~168.7 t of LH 2 propellant.”

Probably not a substantial claim: may not pass S3 (load-bearing). May combine two claims.

For Copernicus-3, each drop tank is about 18.2 m long and the overall vehicle length is about 118.2 m including the 8.9 m Orion MPCV.

“Each drop tank is ~18.2 m long.The overall vehicle length is ~118.2m including the 8.9 m Orion MPCV.”

May combine two claims.

Adding a fourth engine to the NTPS for Copernicus-2 reduces total engine operating time and minimizes g-losses (~326 m/s) during TMI, but increases NTPS inert mass at the expense of LH2 and RCS propellant loading.

“A fourth engine is added to the NTPS to reduce the total engine operating time and minimize g-losses (~326 m/s) during the TMI maneuver but this increases NTPS inert mass at the expense of LH 2 and RCS propellant loading.”

The quote only partly states this claim.

In Copernicus-3, the saddle truss/drop tank assembly is replaced by a 4-sided star truss with twin LH2 drop tanks that supplement propellant carried by the NTPS and in-line tank.

“To achieve transit times in the range of 120 to 100 days, Copernicus' saddle truss/drop tank assembly is replaced by a 4-sided star truss to which paired sets of LH 2 drop tanks are attached as needed.”

May combine two claims.

In Copernicus-2, the in-line and drop tanks are each about 20.5 m long and each carries about 91.5 t of LH2 propellant.

“The in-line and drop tank lengths are the same at ~20.5 m and each tank carries ~91.5 t of LH 2 propellant.”

Classified as probably not a substantial claim. May combine two claims.

For 180-day transits to and from Mars and a 575-day surface stay, the total round-trip time is 935 days and the total ΔV budget excluding gravity losses is 6.045 km/s.

“For 180-day transits to and from Mars and a 575-day stay time at Mars, the total round trip time and V budget (minus g-loss) for the mission are 935 days and 6.045 km/s, respectively.”

May combine two claims.

For Copernicus-3, two drop tanks (~190 t) carrying about 159.4 t of LH2 (~79.7 t per tank) are delivered to LEO on two HLV launches and attached to a ~25.4 m star truss (~20.3 t) during LEO assembly.

“Two drop tanks (~190 t) carrying ~159.4 t of LH 2 (~79.7 t per tank) are delivered to LEO on two HLV launches, then attached to the ~25.4 m long star truss (~20.3 t) during the LEO assembly phase.”

Probably not a substantial claim: may not pass S3 (load-bearing). May combine two claims.

The LH2 drop tank is about 22.7 m long, has a mass of about 21 t, a propellant capacity of about 102.4 t, and is off-loaded to carry about 91.9 t.

“The ~22.7 m long LH 2 drop tank has a mass of ~21 t and a propellant capacity of ~102.4 t but is also off-loaded and only carries ~91.9 t of LH 2 propellant.”

Probably not a substantial claim: may not pass S3 (load-bearing). May combine two claims.

The NTPS LH2 tank has a propellant capacity of about 87.2 t but is off-loaded to carry about 86.8 t for this mission.

“The LH 2 tank has a propellant capacity of ~87.2 t but is slightly off-loaded for this particular mission and carries ~86.8 t.”

Probably not a substantial claim: may not pass S3 (load-bearing), S4 (based).

Four rectangular PVAs of 12.5 kWe and 125 m2 provide about 50 kWe at Mars for crew life support, ZBO Brayton cryocooler operation, and high-data-rate communications with Earth.

“Four 12.5 kW e / 125 m 2 rectangular PVAs provide ~50 kW e of electrical power at Mars for crew life-support (~30 kW e ), a ZBO Brayton cryocooler system (~10 kW e ), and high data-rate communications (~10 kW e ) with Earth.”

May combine two claims.

For Copernicus-3, with 100.4 klbf total thrust and Isp about 906 s, total engine burn time is about 106.4 min, close to the ~2 hr demonstrated on the NRX-XE engine.

“With 100.4 klb f of total thrust and I sp ~906 s, the total engine burn time for this mission is ~106.4min, close to the ~2 hr demonstrated on the NRX-XE engine.”

Probably not a substantial claim: may not pass S3 (load-bearing), S4 (based).

Removing about 78 W of heat penetrating the 60-layer MLI in LEO requires the two-stage cryocooler to use about 8.9 kWe.

“To remove ~78 W of heat penetrating the 60 layer MLI system in LEO (where the highest tank heat flux occurs), the 2-stage cryocooler system requires ~8.9 kW e for its operation.”

Probably not a substantial claim: may not pass S3 (load-bearing).

For Copernicus-2, after the first TMI perigee burn the drop tank is drained and jettisoned to reduce vehicle mass and propellant consumption during the second perigee burn (~21.8 min).

“After this burn, the drop tank is drained and then jettisoned to reduce vehicle mass and propellant consumption during the second perigee burn (~21.8 min).”

Probably not a substantial claim: may not pass S3 (load-bearing), S4 (based). May combine two claims.

An upgraded SLS is used to deliver the crewed payload element and the large but lightweight star truss.

“An upgraded SLS is used to deliver the crewed payload element and the large but lightweight star truss.”

Probably not a substantial claim: may not pass S3 (load-bearing). May combine two claims.

The saddle truss is about 27.7 m long and has a mass of about 9 t.

“It is ~27.7 m long and has a mass of ~9 t.”

May combine two claims.

For Copernicus-3, LH2 loading in the off-loaded NTPS, in-line tank, and twin drop tanks is about 83.1, 98.6, and 159.4 t, respectively.

“The LH 2 loading in the off-loaded NTPS, in-line and twin drop tanks is ~83.1, ~98.6, and ~159.4 t, respectively.”

May combine two claims.

For Copernicus-3, after a long first perigee burn (~52 min), both drop tanks are jettisoned; remaining burn durations are second perigee (~20.7 min), MOC (~22.2 min), and TEI (~11.5 min).

“After completing a long first perigee burn (~52 min), both drop tanks are jettisoned.The remaining burn durations are as follows: second perigee burn (~20.7 min), MOC (~22.2 min) and TEI (~11.5 min).”

May combine two claims.

For Copernicus-3a, the crew size is reduced to four and the mass of TransHab and consumables is reduced accordingly.

“The crew size is reduced to four and the mass of the TransHab and consumables needed for the mission are reduced accordingly.”

May combine two claims.

For Copernicus-2, the NTPS LH2 tank is about 19.7 m long and carries about 86.1 t of propellant, near its maximum capacity of about 87.2 t.

“The LH 2 tank length in the NTPS is ~19.7 m and it carries ~86.1 t of propellant (close to its maximum capacity of ~87.2 t).”

May combine two claims.

Reducing transit times to 90 days increases the Mars stay time to about 673 days and reduces the round-trip time to about 853 days.

“Cutting the transit times in half to 90-days increases the Mars stay time to ~673 days, but decreases the round trip time to ~853 days.”

May combine two claims.

For the 150-day 2033 mission, Copernicus IMLEO includes about 138.8 t for the NTPS, about 125.6 t for the saddle truss and LH2 drop tank, and about 67.3 t for the crew payload section.

“Included are (1) the NTPS (~138.8t); (2) the saddle truss and LH 2 drop tank (~125.6 t); and (3) the crew payload section (~67.3).”

Probably not a substantial claim: may not pass S3 (load-bearing). May combine two claims.

For Copernicus-3, the NTPS and in-line LH2 tanks are about 19.7 and 21.9 m long.

“The lengths of NTPS and in-line LH 2 tanks are ~19.7 and ~21.9 m.”

Probably not a substantial claim: may not pass S4 (based).

With an exhaust temperature of about 2790 K and a nozzle area ratio of about 300:1, the NTR specific impulse is about 906 s.

“With T ex ~2790 K and NAR~300:1, the I sp is ~906 s with higher I sp values achievable by increasing the fuel operating temperature.”

May combine two claims.

In the split mission, the outbound transit time on Copernicus-2 is 100 days and the inbound transit time using the ERV is 90 days.

“The outbound transit time on Copernicus-2 is 100 days and the inbound transit time using the ERV is 90 days.”

Probably not a substantial claim: may not pass S3 (load-bearing), S4 (based). May combine two claims.

On final approach to Earth, the ERV does a final slowdown burn (delta-V ~2.257 km/s), after which the crew separates and re-enters using the Orion MPCV capsule.

“On the final approach to Earth, the ERV does a final slowdown burn (V ~2.257 km/s) after which the crew separates and re-enters using the Orion MPCV capsule.”

Probably not a substantial claim: may not pass S3 (load-bearing).

For Copernicus-3a, the drop tanks are jettisoned in pairs after the first and second perigee burns to reduce vehicle mass and propellant consumption during the TMI maneuver.

“The drop tanks are jettisoned in pairs after the first and second perigee burns to reduce vehicle mass and propellant consumption during the TMI maneuver.”

Probably not a substantial claim: may not pass S4 (based).

Copernicus-3a is a large complex vehicle that requires eight launches to deliver its elements to LEO.

“Copernicus-3a is a large complex vehicle that requires eight launches to deliver the various elements to LEO.”

Probably not a substantial claim: may not pass S3 (load-bearing).

For the outbound Copernicus-2, after the first TMI perigee burn the drop tank is drained and jettisoned to reduce vehicle mass and propellant consumption during the second perigee burn (~28.8 min).

“After this burn, the drop tank is drained and jettisoned to reduce vehicle mass and propellant consumption during the second perigee burn (~28.8 min).”

Probably not a substantial claim: may not pass S3 (load-bearing). May combine two claims.

The ERV performs the TEI burn on July 1, 2035 and begins the 90-day transfer back to Earth.

“The ERV then performs the TEI burn on July 1, 2035 and begins the 90-day transfer back to Earth.”

May combine two claims.

The Copernicus-3a payload element includes the Orion MPCV (~15.1 t), which carries additional propellant (~5.1 t) for the final Earth slowdown burn (delta-V ~1.266 km/s) before re-entry while the MTV flies past Earth and is disposed of in heliocentric space.

“The PL element includes the Orion MPCV (~15.1 t) which carries additional propellant (~5.1 t) for the final Earth slowdown burn (V ~1.266 km/s) before re-entry while the MTV flies past Earth and is disposed of in heliocentric space.”

Probably not a substantial claim: may not pass S3 (load-bearing).

Copernicus-3a uses composite LH2 tanks instead of Al/Li.

“Composite LH 2 tanks are also used instead of Al/Li.”

Probably not a substantial claim: may not pass S3 (load-bearing), S4 (based).

Seven HLV launches are required to deliver the major Copernicus-3a transportation systems elements (NTPS, in-line tank, four drop tanks, and PL element) to LEO.

“Seven HLV launches are required to deliver the major transportation systems elements (the NTPS, in-line tank, four drop tanks, and PL element) to LEO.”

Probably not a substantial claim: may not pass S3 (load-bearing).

Copernicus-3a's overall vehicle length is about 117.6 m.

“The overall vehicle length is ~117.6 m.”

May combine two claims.

Copernicus-3a's four drop tanks carry about 327.8 t of propellant (~82 t per tank), and each tank is about 18.6 m long.

“Copernicus-3a's four drop tanks carry ~327.8 t of propellant (~82 t per tank), and each tank is ~18.6 m long.”

• Also stated in: § 6.0 Summary and Conclusions · plain

  “Four drop tanks-each carrying ~82 t of propellant-are also used.”

May combine two claims.

The ERV arrives at Mars and propulsively captures into a 24-hr elliptical Mars orbit (~250 by 33,793 km) in October 2031, where it remains until the crewed Copernicus-2 MTV arrives during the next opportunity about 26 months later.

“The ERV then arrives at Mars (arrival V inf ~3.480 km/s) and propulsively captures into a 24-hr elliptical Mars orbit (~250 by 33,793 km, V MOC ~1.34 km/s) in October 2031 where it remains until the crewed Copernicus-2 MTV arrives during the next opportunity ~26 months later.”

Probably not a substantial claim: may not pass S3 (load-bearing), S4 (based).

Before leaving Mars orbit, the crew jettisons the exterior consumables container and connecting tunnel from the PL element to reduce vehicle mass and propellant consumption.

“Before leaving Mars orbit, the crew finally jettisons the exterior consumables container and connecting tunnel from the PL element to reduce vehicle mass and propellant consumption.”

Probably not a substantial claim: may not pass S3 (load-bearing). May combine two claims.

Copernicus-3a's first perigee burn is the longest single burn at about 78.3 min and exceeds the single burn duration record of about 62 min set by the NRX-A6 engine.

“The first perigee burn is the longest single burn at ~78.3 min and also exceeds the single burn duration record of ~62 min set by the NRX-A6 engine.”

May combine two claims.

For Copernicus-3a, remaining burn durations are second perigee (~37.3 min), MOC (~33.3 min), and TEI (~16.5 min).

“The duration of the remaining burns are as follows: second perigee burn (~37.3 min), MOC (~33.3 min), and TEI (~16.5 min).”

Probably not a substantial claim: may not pass S3 (load-bearing), S4 (based). May combine two claims.

The ERV flies past Earth at a sufficiently high altitude and is disposed of into heliocentric space.

“The ERV flies past Earth at a sufficiently high altitude and is disposed of into heliocentric space.”

Probably not a substantial claim: may not pass S4 (based). May combine two claims.

Copernicus-2 departs LEO with its four crew on May 25, 2033 and arrives at Mars 100 days later.

“Copernicus-2 departs LEO with its four crew on May 25, 2033 and arrives at Mars 100 days later.”

May combine two claims.

Using Copernicus-2 plus an ERV, a 2033 landing mission would require a round trip time of about 857 days, with about 667 days spent in Mars orbit and on the surface.

“Using the Copernicus-2 spacecraft plus an ERV, a 2033 landing mission would require a round trip time of ~857 days with ~667 days spent in Mars orbit and on the surface.”

Probably not a substantial claim: may not pass S3 (load-bearing), S4 (based).

A single SLS with sufficient PL volume will be used to launch the large but lightweight star truss for Copernicus-3a.

“A single SLS with sufficient PL volume will be used to launch the large but lightweight star truss.”

May combine two claims.

Copernicus-3a has an IMLEO of about 720.7 t, including NTPS (~137.6 t), in-line tank (~123.7 t), star truss with four common LH2 drop tanks (~397.5 t), and crew payload section (~61.9 t).

“The resulting vehicle has an IMLEO of ~720.7 t, which includes the NTPS (~137.6 t), the in-line tank (~123.7 t), the star truss with four common LH 2 drop tanks (~397.5 t) and the crew PL section (~61.9 t).”

Probably not a substantial claim: may not pass S3 (load-bearing), S4 (based).

In the process, Copernicus-2 uses up about 97 percent of its available propellant.

“In the process, Copernicus-2 uses up ~97 percent of its available propellant.”

May combine two claims.

The total and longest single engine burn times required for the ERV mission, while substantial, are still below the capabilities demonstrated by the NRX-XE (~2 hr) and NRX-A6 engines (~62 min).

“The total and longest single engine burn times required for the ERV mission while substantial, are still below the capabilities demonstrated by the NRX-XE (~2 hr) and NRX-A6 engines (~62 min).”

• Also stated in: § 6.0 Summary and Conclusions · boosted

  “Finally, it is important to note that both the total and longest single engine burn times required for the split mission, while substantial, are still below the capabilities demonstrated by the NRX-XE (~2 hr) and NRX-A6 engines (~62 min).”

May combine two claims.

The ERV's NTPS performs five primary burns (and four restarts) and its three engines provide about 75.3 klbf total thrust.

“The ERV's NTPS performs five primary burns (and four restarts) and its three engines provide ~75.3 klb f of total thrust.”

Probably not a substantial claim: may not pass S3 (load-bearing), S4 (based).

From the initial launch of the NTPS until the last drop tank is attached to the star truss via orbital assembly could take about 7 months, assuming 30 days between SLS/HLV launches.

“From the initial launch of the NTPS until the last drop tank is attached to the star truss (via orbital assembly) could take ~7 months assuming 30 days between SLS/HLV launches.”

• AssumptionThe authors state this as an assumption: For the Copernicus-3a orbital assembly timeline, there are 30 days between SLS/HLV launches.

Probably not a substantial claim: may not pass S3 (load-bearing). May combine two claims.

After about 653 days on the surface, the crew lifts off using the MAV and returns to the ERV.

“After ~653 days on the surface, the crew lifts off using the MAV and returns to the ERV.”

Probably not a substantial claim: may not pass S4 (based). May combine two claims.

The HLV launch count increases from about 5 to 7 and a fourth engine is needed to reduce total mission burn time and gravity losses.

“The HLV launch count increases (from ~5 to 7) and a fourth engine is needed to reduce total mission burn time and gravity losses.”

May combine two claims.

No on-orbit assembly (e.g., attachment of multiple drop tanks) is required for the split mission, only autonomous R&D of several vehicle components.

“No on-orbit assembly (e.g., attachment of multiple drop tanks) is required just autonomous R&D of several vehicle components.”

• Also stated in: § Additional information · plain

  “The split mission approach also eliminates the need for on-orbit assembly.”

Probably not a substantial claim: may not pass S3 (load-bearing), S4 (based).

Copernicus-2 captures into the same parking orbit as the ERV on September 2, 2033.

“It then captures into the same parking orbit as the ERV on September 2, 2033.”

May combine two claims.

The NTPS, in-line, and drop tank elements of the outbound Copernicus-2 (using composite tanks) carry about 87.2, 71.3, and 95 t of LH2, respectively, for a total LH2 propellant loading of about 253.5 t.

“The NTPS, in-line and drop tank elements (again using composite tanks) carry ~87.2, ~71.3, and ~95 t respectively, for a total LH 2 propellant loading of ~253.5 t.”

May combine two claims.

For Copernicus-3a, the NTPS and in-line LH2 tanks are about 19.7 and 21.9 m long and carry about 87.2 and 95.5 t of propellant, respectively.

“The LH 2 tank lengths in the NTPS and in-line element are ~19.7 and ~21.9 m, and they carry ~87.2 and ~95.5 t of propellant, respectively.”

May combine two claims.

For the ERV, remaining burn durations are second perigee (~13.7 min), MOC (~13 min), TEI (~28.6 min), and final slowdown burn (~15.5 min).

“The durations of the remaining burns are as follows: second perigee burn (~13.7 min), MOC (~13 min), TEI (~28.6 min), and final slowdown burn (~15.5 min).”

Probably not a substantial claim: may not pass S4 (based).

The total usable propellant for the Copernicus-3a mission is about 480.7 t.

“The total usable propellant for the mission is ~480.7 t.”

May combine two claims.

The composite tanks used in the ERV's NTPS, in-line, and drop tank elements carry about 87.2, 77, and 95 t of propellant, respectively, for a total propellant loading of about 259.2 t.

“The composite tanks used in the ERV's NTPS, in-line and drop tank elements carry ~87.2, ~77, and ~95 t respectively, for a total propellant loading of ~259.2 t.”

Probably not a substantial claim: may not pass S4 (based). May combine two claims.

To return to Earth, Copernicus-2 rendezvous with the ERV and the forward crewed PL element is switched over to the ERV; no propellant transfer is required, only a R&D maneuver.

“To return to Earth, Copernicus-2 rendezvous with the ERV and the forward crewed PL element is switched over to the ERV (shown in Fig. 13).No propellant transfer is required just a R&D maneuver.”

May combine two claims.

DRA 5.0 selected the fast conjunction/long stay Mars mission option as its baseline because it has lower total ΔV, a long surface stay, short transit times, and no Venus swing-by.

“Because of its attractive features-lower total V, a long surface stay, short transit times, and no VSB-the fast conjunction/long stay mission option was selected as the baseline for DRA 5.0.”

• cites Ref. 1Not matched

  Couldn’t be matched to a paper in Crossref, so it can’t be checked.

May combine two claims.

NTP is a proven technology that was ground tested at the performance levels needed for a human Mars mission.

“NTP is a proven technology successfully ground tested at the performance levels required for a human mission to Mars.”

• cites Ref.8Not matched

  Couldn’t be matched to a paper in Crossref, so it can’t be checked.

Probably not a substantial claim: may not pass S3 (load-bearing), S4 (based). May combine two claims.

The propellant tank heat load is largest in LEO, and it determines the size of the ZBO cryocooler system.

“The propellant tank heat load is largest in LEO and sizes the ZBO cryocooler system.”

May combine two claims.

Adding oxygen in LANTR lowers Isp to about 725 s, still about 270 s higher than LOX/LH2 engines.

“The addition of oxygen lowers the I sp to ~725 s but this is still ~270 s higher than that achieved by LOX/LH 2 engines.”

• cites Refs.20 and 21Not matched

  Couldn’t be matched to a paper in Crossref, so it can’t be checked.

May combine two claims.

A fast conjunction Mars mission with a one-year deep-space journey could deliver about 0.66 Sv to astronauts, which is NASA's limiting dose.

“indicating that astronauts could receive a radiation dose of ~0.66 Sv (~66 rem)-the limiting value established by NASA-during a fast conjunction Mars mission involving a 1-year journey through deep space.”

• cites Ref.6Not matched

  Couldn’t be matched to a paper in Crossref, so it can’t be checked.

May combine two claims.

Pewee set records for the highest average fuel-element exit gas temperature, about 2550 K, and the highest peak fuel temperature, about 2750 K.

“It set several performance records including the highest average fuel element exit gas temperature of ~2550 K, and the highest peak fuel temperature ~2750 K.”

• cites Ref.8Not matched

  Couldn’t be matched to a paper in Crossref, so it can’t be checked.

Probably not a substantial claim: may not pass S3 (load-bearing), S4 (based). May combine two claims.

Because solar radiation at Mars is about 486 W/m2, solar array areas can become quite large, about 10 m2/kWe, requiring multiple arrays for human Mars missions.

“Because of the decreased solar radiation at Mars (~486 W/m 2 ), array areas can become quite large (~10 m 2 /kW e ) necessitating multiple arrays for human Mars missions.”

May combine two claims.

Pewee achieved average and peak reactor-core power densities of about 2340 MWt/m3 and 5200 MWt/m3, respectively.

“Other performance records included average and peak power densities in the reactor core of ~2340 MW t /m 3 and ~5200 MW t /m 3 , respectively.”

• cites Ref.8Not matched

  Couldn’t be matched to a paper in Crossref, so it can’t be checked.

May combine two claims.

No integrated reactor/engine tests were done for cermet fuel, but many specimens were produced and tested in non-nuclear hot hydrogen and irradiation tests with promising results.

“While no integrated reactor/engine tests were conducted, a large number of fuel specimens were produced and exposed to non-nuclear hot H 2 and irradiation testing with promising results.”

• cites Refs.16 and 17Not matched

  Couldn’t be matched to a paper in Crossref, so it can’t be checked.

May combine two claims.

The baseline Copernicus design can achieve one-way transit times of about 150 to 220 days depending on the opportunity, and 150-day transit times are possible for the 2033 mission.

“The baseline Copernicus design is capable of 1-way transit times ranging from ~150 to 220 days depending on the particular opportunity.For the 2033 mission, 150-day transit times are possible.”

• cites Ref.9Not matched

  Couldn’t be matched to a paper in Crossref, so it can’t be checked.

May combine two claims.

The optimum tank diameter and mass for a Mars NTPS are 10 m and about 140 t.

“The optimum tank diameter and mass for a Mars NTPS are 10 m and ~140 t (Ref.9).”

• cites Ref.9Not matched

  Couldn’t be matched to a paper in Crossref, so it can’t be checked.

May combine two claims.

Plenty of time for scientific investigation and study, coupled with short ~6-month transit times to reduce crew exposure to 0-g and radiation environments, were key reasons for selecting the fast conjunction long surface stay mission.

“Plenty of time for scientific investigation and study, coupled with short ~6-month transit times to reduce crew exposure to the 0-g E and radiation environments of space were key reasons for this selection.”

May combine two claims.

The key requirements for further transit time reductions are more propellant and reduced U-235 loading in the engine's reactor fuel elements to allow higher operating temperatures.

“The key requirements are more propellant and reduced U-235 loading in the engine's reactor fuel elements to allow higher operating temperatures.”

Probably not a substantial claim: may not pass S3 (load-bearing). May combine two claims.

Use of a pre-deployed ERV is not a new idea; in NASA's DRM 1.0 study in 1993, the ERV was one of the key transportation system elements used in the mission architecture.

“Use of a pre-deployed ERV is not a new idea.In NASA's DRM 1.0 study in 1993 (Ref.22), the ERV was one of the key transportation system elements used in the mission architecture.”

• cites Ref.22Not matched

  Couldn’t be matched to a paper in Crossref, so it can’t be checked.

May combine two claims.

The long TEI burn for the ERV is attributed to the addition of Copernicus-2's ~40.2 t crewed PL mass plus the high TEI delta-V requirement (~3.075 km/s) for the 90-day transit back to Earth.

“The long TEI burn is attributed to the addition of Copernicus-2's ~40.2 t crewed PL mass plus the high TEI V requirement (~3.075 km/s) for the 90-day transit back to Earth.”

May combine two claims.

NTP was identified as the preferred propulsion option because of its high performance (100 percent higher Isp than LOX/LH2 chemical propulsion), its demonstrated technology record, and strong synergy with chemical propulsion systems and stages.

“Similarly, NTP was identified as the preferred propulsion option because of its high performance (100 percent higher I sp than LOX/LH 2 chemical propulsion), its demonstrated technology record, plus the strong synergy that exists between it and chemical propulsion systems and stages.”

Classified as probably not a substantial claim. May combine two claims.

Failure to deliver the elements on time and in the prescribed order could delay vehicle assembly and jeopardize mission departure within the specified launch window.

“Failure to deliver the elements on time and in the prescribed order could delay vehicle assembly and jeopardize mission departure within the specified launch window.”