# US 12,110,134 B1 · Orbital rendezvous techniques

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- Number: US 12,110,134 B1
- Document ID: US12110134B1
- Status: Granted
- Kind: B1
- Application number: 17/739,535
- Filed: 2022-05-09
- Granted: 2024-10-08
- Earliest claimed: 2019-05-01
- Assignees: United Launch Alliance, L.L.C.
- Applicants: United Launch Alliance, L.L.C.
- Inventors: Eric W. Monda; Bernard F. Kutter
- Web page: https://patentgrep.com/patent/US12110134B1

## CPC

- B64G 1/646: {Docking or rendezvous systems (refuelling in space B64G1/4024)}
- B64G 1/002: {Launch systems}
- B64G 1/2427: {Transfer orbits}
- B64G: COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR

## Abstract

A method of achieving orbital rendezvous with a target satellite includes launching a spacecraft with a launch vehicle at an optimal time; steering the launch vehicle out-of-plane based on the orbital elements of the target satellite's orbit; and entering a predetermined rendezvous envelope of the target satellite before the target satellite completes one complete orbit from the target satellite's position at the optimal time.

## Claims

### Claim 1

A method of achieving orbital rendezvous comprising:
launching a spacecraft from a fixed launch site at an optimal launch time of a given day, where the optimal launch time is selected to yield a target phase angle between the spacecraft and a target satellite on a preferred pass of the target satellite relative to the launch site on the given day, the target satellite orbiting in an orbital plane that does not pass through the launch site;
using a 2-burn launch profile of the launch vehicle to first insert the spacecraft into a parking orbit with a first burn; and
executing, from the parking orbit, a rendezvous envelope insertion maneuver with a second burn to cause the spacecraft to enter a rendezvous envelope before the target satellite completes a full orbit from its position at the optimal launch time.

### Claim 2 (depends on 1)

The method of claim 1, wherein a closed-loop guidance algorithm is used to insert the spacecraft into the parking orbit.

### Claim 3 (depends on 1)

The method of claim 1, wherein the parking orbit has an apogee between about 375 and 450 km.

### Claim 4 (depends on 1)

The method of claim 1, further comprising:
docking or berthing the spacecraft with the target satellite.

### Claim 5 (depends on 1)

The method of claim 1, wherein the target satellite is the International Space Station.

### Claim 6 (depends on 1)

The method of claim 1, wherein the target satellite is in low Earth orbit.

### Claim 7 (depends on 1)

The method of claim 1, wherein the spacecraft is launched from the launch site aboard a two-stage launch vehicle.

### Claim 8 (depends on 7)

The method of claim 7, wherein a second stage of the two-stage launch vehicle executes a rendezvous envelope insertion maneuver.

### Claim 9 (depends on 7)

The method of claim 7, wherein a second stage of the two-stage launch vehicle carries the spacecraft.

### Claim 10

A launch system comprising:
a launch vehicle comprising a lower stage and at least one upper stage; and
a control unit comprising:
a processor;
a communication interface; and
a memory, the memory storing instructions for execution by the processor that, when executed, cause the processor to:
initiate launch of the launch vehicle from a fixed launch site at an optimal time of a selected day, the optimal time coinciding with a target phase angle between the launch vehicle and a target satellite, the target satellite having an orbit in an orbital plane that does not pass through the launch site, the orbit defined by orbital elements;
issue out-of-plane steering commands based on the orbital elements; and
execute two engine burns that cause at least the at least one upper stage to enter, in less than one complete orbit of the target satellite from the optimal launch time, a rendezvous envelope of the target satellite.

### Claim 11 (depends on 10)

The launch system of claim 10, wherein the memory stores additional instructions for execution by the processor that, when executed by the processor, cause the processor to control a trajectory of the launch vehicle to insert at least the upper stage into a parking orbit, and further wherein the engine burn comprises a rendezvous envelope insertion maneuver sufficient to cause the at least one upper stage to enter the rendezvous envelope.

### Claim 12 (depends on 11)

The launch system of claim 11, wherein controlling the trajectory of the launch vehicle to insert at least the at least one upper stage into the parking orbit comprises executing a closed-loop guidance algorithm.

### Claim 13 (depends on 11)

The launch system of claim 11, wherein the memory stores additional instructions for execution by the processor that, when executed by the processor, cause the processor to:
delay initiation of the rendezvous envelope insertion maneuver by the at least one upper stage until a predetermined amount of time has passed after insertion of the upper stage into the parking orbit.

### Claim 14 (depends on 10)

The launch system of claim 10, wherein the optimal time further coincides with a preferred pass of the target satellite relative to the launch site on the selected day.

### Claim 15 (depends on 10)

The launch system of claim 10, wherein the at least one upper stage carries a spacecraft, and further wherein the memory stores additional instructions for execution by the processor that, when executed by the processor, cause the processor to:
initiate separation of the spacecraft from one of the at least one upper stage in the rendezvous envelope.

### Claim 16 (depends on 10)

The launch system of claim 10, wherein the launch vehicle comprises the control unit.

### Claim 17

A method of rendezvousing with a target satellite, comprising:
initiating a launch sequence to achieve launch of a launch vehicle from a fixed launch site based on an optimal time, the optimal time determined to yield a predetermined phase angle between the launch vehicle and a target satellite;
causing the launch vehicle to steer during launch toward a predetermined rendezvous envelope of the target satellite via a 1-burn launch profile, wherein the target satellite is orbiting in an orbital plane that does not pass through the launch site at the optimal time; and
inserting at least a portion of the launch vehicle into the rendezvous envelope of the target satellite before the target satellite completes one complete orbit from the target satellite's position at the optimal time.

### Claim 18 (depends on 17)

The method of claim 17, further comprising:
controlling the launch vehicle to insert the at least a portion of the launch vehicle directly into the rendezvous envelope of the target satellite.

### Claim 19 (depends on 17)

The method of claim 17, wherein the launch vehicle carries a spacecraft, and the method further comprises:
causing the spacecraft to dock or berth with the target satellite.