Orbital mechanics of impulsive launch

Abstract

Methods of launching a vehicle using impulsive force are disclosed. In one instance, a vehicle is launched easterly with impulsive force in a plane corresponding to the vehicle's elliptical orbital path. In another instance, a method of closing a timing difference is disclosed. The vehicle undergoes a series of forces after impulsive launch. The first force establishes an orbit having a period significantly different from the orbital period of a satellite or desired vehicle location, closing the difference in an integer number of orbits. The second force establishes the vehicle in circular orbit with the satellite or desired vehicle location. In another instance, the vehicle launched impulsively from a first celestial body travels a first path, and the vehicle experiences a second force along a hyperbolic path about the second celestial body and enters circular orbit about the second celestial body.

What is claimed is: 
     
         1 . A method for a vehicle launch from a first celestial body and to an orbit about a launch destination other than the first celestial body, said method comprising
 a. launching the vehicle using a first force comprising an impulsive force to provide a first vehicle path;   b. applying a second force to the vehicle along a hyperbolic path about the launch destination; and   c. establishing an orbit about the launch destination.   
     
     
         2 . A method according to  claim 1 , wherein the method additionally comprises launching the vehicle in an easterly direction. 
     
     
         3 . A method according to  claim 2 , wherein the direction is due east. 
     
     
         4 . A method according to  claim 1 , wherein the launch destination is a LaGrange point. 
     
     
         5 . A method according to  claim 4 , wherein the first celestial body and the LaGrange point are each in orbit about a second celestial body. 
     
     
         6 . A method according to  claim 5 , wherein the first celestial body is the Moon or a planet orbiting the Sun and the second celestial body is the Sun. 
     
     
         7 . A method according to  claim 4 , wherein the LaGrange Point and a second celestial body are each in orbit about the first celestial body. 
     
     
         8 . A method according to  claim 7 , wherein the first celestial body is a planet orbiting the Sun and the second celestial body is a moon of the first celestial body. 
     
     
         9 . A method according to  claim 8 , wherein the first celestial body is the Earth and the second celestial body is the Moon. 
     
     
         10 . A method according to  claim 1 , wherein the launch destination is a second celestial body, and the first celestial body and the second celestial body are each in orbit about a third celestial body. 
     
     
         11 . A method according to  claim 10 , wherein the second celestial body is a planet such as Mars in orbit about the Sun, the first celestial body is Earth, and the third celestial body is the Sun. 
     
     
         12 . A method according to  claim 1 , wherein the impulsive force is provided by a member selected from the group consisting of a light gas gun, an electromagnetic launcher, and a land-based or a sea-based impulsive launcher. 
     
     
         13 . A method according to  claim 12 , wherein the launch vehicle is a single stage launch vehicle. 
     
     
         14 . A method according to  claim 1 , wherein
 a. the step of launching the vehicle comprises launching the vehicle at a latitude of about 23.4 deg north or about 23.4 deg south in a direction due east,   b. the first vehicle path is hyperbolic about the first celestial body, and   c. the step of establishing the orbit about the launch destination comprises applying a third force to the vehicle to establish the vehicle in said orbit about the launch destination.   
     
     
         15 . A method according to  claim 14 , wherein the third force places the vehicle's orbit in a plane of the launch destination's orbit. 
     
     
         16 . A method according to  claim 1 , wherein the method additionally comprises placing the vehicle in Earth orbit and rendezvousing with a man-made object selected from the group consisting of a space station, a supply vehicle, a supply depot, and a crewed capsule prior to step (b) of  claim 1 . 
     
     
         17 . A method according to  claim 1 , wherein the vehicle comprises a supply vehicle in said orbit about the launch destination, and the supply vehicle provides at least one member selected from the group consisting of fuel, equipment, construction supplies, parts, food, and beverages. 
     
     
         18 . A method according to  claim 1 , wherein the first vehicle path is composed of a first ballistic portion and a second portion departing from the ballistic portion near a ballistic apogee at zero flight path angle to proceed to the launch destination. 
     
     
         19 . A method according to  claim 18 , wherein the first celestial body is the Earth and the launch destination is the Moon. 
     
     
         20 . A method according to  claim 18 , wherein the first celestial body is the Earth and the launch destination is the planet Mars, and the second portion provides a path that is heliocentric and hyperbolic with respect to Mars. 
     
     
         21 . A method according to  claim 18 , wherein the first celestial body is the Moon. 
     
     
         22 . A method according to  claim 21 , wherein the launch vehicle is a single stage launch vehicle. 
     
     
         23 . A method according to  claim 18 , wherein the first celestial body is Mars. 
     
     
         24 . A method according to  claim 23 , wherein the launch vehicle is a single stage launch vehicle.