Soft Electric Landing on Luna - Revision history

Michel Lamontagne at 03:30, 18 October 2022

2022-10-18T03:30:29Z

Michel Lamontagne: /* Sizing the landing system */

2022-10-18T03:21:17Z

Sizing the landing system

Michel Lamontagne at 03:19, 18 October 2022

2022-10-18T03:19:54Z

Michel Lamontagne at 03:14, 18 October 2022

2022-10-18T03:14:46Z

Farred: add See Also

2013-06-04T16:30:02Z

add See Also

Farred: adding links

2010-06-24T04:27:04Z

adding links

Farred: Soft Electric Landing on Luna

2010-06-10T15:15:57Z

Soft Electric Landing on Luna

New page

Soft electric landing on Luna can be provided for an orbiting spacecraft in the following way. The spacecraft lines up with the runway on the equator at the same spot from which spacecraft are launched to L2. The incoming orbit is right down the middle of a rectangular cross section ditch. Two slots, one on each side of the ditch, lead to the linear electric motors that power the catcher that also races down this ditch. Structural members of the catcher disappear into these slots terminating in the moving portion of the linear electric motors. The spacecraft maneuvers so that its orbit brings it to the right place with the right velocity. The catcher adjusts its run to be there at the right time for a rendezvous. After catching the spacecraft, the catcher brakes electromagnetically, saving the energy as electricity.

This arrangement is easier than soft landing by tether because a tether cannot adjust the time that it arrives at a rendezvous with a spacecraft.

[[category:Space Transport]]

@@ Line 4: / Line 4: @@
 *Two slots, one on each side of the ditch, lead to the linear electric motors that power the catcher that also races down this ditch.
 *Structural members of the catcher disappear into these slots terminating in the moving portion of the linear electric motors.
 *The spacecraft maneuvers so that its orbit brings it to the right place with the right velocity.
 *The catcher adjusts its run to be there at the right time for a rendezvous.
-*After catching the spacecraft, the catcher brakes electromagnetically, saving the energy as electricity that must be stored in an accululator, such as a capacitor bank, batteries or induction rings. This energy can later be used to launch payloads.
+*After catching the spacecraft, the catcher brakes electromagnetically, saving the energy as electricity that must be stored in an accumulator, such as a capacitor bank, batteries or induction rings. This energy can later be used to launch payloads.
 This arrangement may be easier than soft landing by tether because a tether cannot adjust the time that it arrives at a rendezvous with a spacecraft.
 The facility described above is a high capacity version of a [[Mass Drivers|mass driver]].
 The same track should probably be usable for launching.
@@ Line 17: / Line 20: @@
 Orbital velocity= v = 1680 m/s  if we add 10% to elevate the orbit a bit, with let's say 1800 m/s
 for an acceleration (a) of 2g, or 20 m/s2, the time required is 90 seconds.
 In that time d=a*t^2/2 = 81 000m or 81 km.
 The energy stored is equal to th kinetic energy of the vehicle, plus the potential energy in the elevation of the overall orbit.
 With the same velocity of 1800 m/s
-Each kg caught would deliver e=1/2mv2 = 1800*1800/2 = 1 620 000 J or 1,6 MJ per kg minus the system energy losses.
+Each kg caught would deliver e=1/2mv2 = 1800*1800/2 = 1 620 000 J or 1,6 MJ (0,45 kWh) per kg minus the system energy losses.
-Launching to orbit would require the same energy, while launching to escape velocity would require 2380 km/s or 2,8 MJ plus the energy losses in the system.
+Launching to orbit would require the same energy, while launching to escape velocity would require 2380 km/s or 2,8 MJ (0,78 kWh) plus the energy losses in the system.
 == See Also ==

@@ Line 21: / Line 21: @@
 The energy stored is equal to th kinetic energy of the vehicle, plus the potential energy in the elevation of the overall orbit.
 With the same velocity of 1800 m/s
-Each kg caught would deliver e=1/2mv2 = 1800*1800/2 = 1 620 000 J or 1,6 MJ per kg.
+Each kg caught would deliver e=1/2mv2 = 1800*1800/2 = 1 620 000 J or 1,6 MJ per kg minus the system energy losses.
 == See Also ==

@@ Line 6: / Line 6: @@
 *The spacecraft maneuvers so that its orbit brings it to the right place with the right velocity.
 *The catcher adjusts its run to be there at the right time for a rendezvous.
-*After catching the spacecraft, the catcher brakes electromagnetically, saving the energy as electricity that must be sotred in an accululator, such as a capacitor bank, batteries or induction rings.
+*After catching the spacecraft, the catcher brakes electromagnetically, saving the energy as electricity that must be stored in an accululator, such as a capacitor bank, batteries or induction rings. This energy can later be used to launch payloads.
 This arrangement may be easier than soft landing by tether because a tether cannot adjust the time that it arrives at a rendezvous with a spacecraft.
@@ Line 12: / Line 12: @@
 The facility described above is a high capacity version of a [[Mass Drivers|mass driver]].
 This is landing at orbital speed, and would require a very long track to keep acceleration low. As V=a*t
 Orbital velocity= v = 1680 m/s  if we add 10% to elevate the orbit a bit, with let's say 1800 m/s
@@ Line 17: / Line 19: @@
 In that time d=a*t^2/2 = 81 000m or 81 km.
-The same track should probably be usable for launching.
+The energy stored is equal to th kinetic energy of the vehicle, plus the potential energy in the elevation of the overall orbit.

@@ Line 1: / Line 1: @@
-Soft electric landing on Luna can be provided for an orbiting spacecraft in the following way.  The spacecraft lines up with the runway on the equator at the same spot from which spacecraft are launched to [[GFDL:Lagrangian point|L2]].  The incoming orbit is right down the middle of a rectangular cross section ditch.  Two slots, one on each side of the ditch, lead to the linear electric motors that power the catcher that also races down this ditch.  Structural members of the catcher disappear into these slots terminating in the moving portion of the linear electric motors.  The spacecraft maneuvers so that its orbit brings it to the right place with the right velocity.  The catcher adjusts its run to be there at the right time for a rendezvous.  After catching the spacecraft, the catcher brakes electromagnetically, saving the energy as electricity.
+Soft electric landing on Luna can be provided for an orbiting spacecraft in the following way.
-This arrangement is easier than soft landing by tether because a tether cannot adjust the time that it arrives at a rendezvous with a spacecraft.
+This arrangement may be easier than soft landing by tether because a tether cannot adjust the time that it arrives at a rendezvous with a spacecraft.
 == See Also ==
 * [[Eddy Current Brake to Orbit]]

← Older revision		Revision as of 16:30, 4 June 2013
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	The facility here described is a high capacity far future version of a [[Mass Drivers\|mass driver]].		The facility here described is a high capacity far future version of a [[Mass Drivers\|mass driver]].
		+
		+	== See Also ==
		+	* [[Eddy Current Brake to Orbit]]
		+	* [[Driving on the Moon]]

	[[category:Space Transport]]		[[category:Space Transport]]

← Older revision		Revision as of 04:27, 24 June 2010
Line 1:		Line 1:
−	Soft electric landing on Luna can be provided for an orbiting spacecraft in the following way. The spacecraft lines up with the runway on the equator at the same spot from which spacecraft are launched to L2. The incoming orbit is right down the middle of a rectangular cross section ditch. Two slots, one on each side of the ditch, lead to the linear electric motors that power the catcher that also races down this ditch. Structural members of the catcher disappear into these slots terminating in the moving portion of the linear electric motors. The spacecraft maneuvers so that its orbit brings it to the right place with the right velocity. The catcher adjusts its run to be there at the right time for a rendezvous. After catching the spacecraft, the catcher brakes electromagnetically, saving the energy as electricity.	+	Soft electric landing on Luna can be provided for an orbiting spacecraft in the following way. The spacecraft lines up with the runway on the equator at the same spot from which spacecraft are launched to [[GFDL:Lagrangian point\|L2]]. The incoming orbit is right down the middle of a rectangular cross section ditch. Two slots, one on each side of the ditch, lead to the linear electric motors that power the catcher that also races down this ditch. Structural members of the catcher disappear into these slots terminating in the moving portion of the linear electric motors. The spacecraft maneuvers so that its orbit brings it to the right place with the right velocity. The catcher adjusts its run to be there at the right time for a rendezvous. After catching the spacecraft, the catcher brakes electromagnetically, saving the energy as electricity.
		+
		+	This arrangement is easier than soft landing by tether because a tether cannot adjust the time that it arrives at a rendezvous with a spacecraft.

−	~~This arrangement is easier than soft landing by tether because a tether cannot adjust the time that it arrives at a rendezvous with a spacecraft.~~

		+	The facility here described is a high capacity far future version of a [[Mass Drivers\|mass driver]].

	[[category:Space Transport]]		[[category:Space Transport]]