Stackable spacecraft

Patent metadata

Field	Value
Publication number	US-11072441-B2
Application number	US-201715449368-A
Country	US
Kind code	B2
Filing date	Mar 3, 2017
Priority date	Mar 3, 2017
Publication date	Jul 27, 2021
Grant date	Jul 27, 2021

Abstract

A three-axis spacecraft including a spacecraft body including first and second opposing radiator/equipment panels, first and second opposing mounting panels, an earth deck and a zenith deck. The zenith deck faces the Earth when the spacecraft is on orbit and the first and second mounting panels face an east and west direction relative to the Earth when the spacecraft is on orbit. The spacecraft further includes a mounting cylinder extending through the spacecraft body and out of the first and second mounting panels.

First claim

What is claimed is:

1. A three-axis spacecraft comprising:
a spacecraft body being rectangular in shape and including first and second opposing radiator/equipment panels, first and second opposing mounting panels, an earth deck thermally coupled to the first radiator/equipment panel and a zenith deck thermally coupled to the second radiator/equipment panel, wherein the first and second radiator/equipment panels face a north and south direction relative to the Earth when the spacecraft is on orbit, the first and second mounting panels face an east and west direction relative to the Earth when the spacecraft is on orbit, the earth deck faces the Earth when the spacecraft is on orbit, and the zenith deck faces away from the Earth when the spacecraft is on orbit;
a plurality of antennas mounted to the earth deck; and
a mounting cylinder extending through the spacecraft body and out of the first and second mounting panels, wherein the mounting cylinder includes a mounting flange at each end of the cylinder and being operable to be mounted to a mounting flange of a mounting cylinder of other spacecraft.

2. The spacecraft according to claim 1 further comprising a first solar panel mounted to the first radiator/equipment panel and extending therefrom and a second solar panel mounted to the second radiator/equipment panel and extending therefrom.

3. The spacecraft according to claim 1 wherein the plurality of antennas mounted to the earth deck include at least one phased array.

4. The spacecraft according to claim 3 wherein the at least one phased array includes a downlink phased array and an uplink phased array.

5. The spacecraft according to claim 1 wherein the plurality of antennas mounted to the earth deck include at least one cross-link antenna.

6. The spacecraft according to claim 5 wherein the at least one cross-link antenna includes a plurality of cross-link antennas.

7. The spacecraft according to claim 1 wherein the plurality of antennas mounted to the earth deck includes at least one gimbal dish antenna.

8. The spacecraft according to claim 1 further comprising at least one antenna mounted to the zenith deck.

9. The spacecraft according to claim 1 further comprising one or more con-focal reflectors mounted to one or both of the earth deck or the zenith deck.

10. The spacecraft according to claim 1 wherein the spacecraft is selected from the group consisting of medium power geostationary orbit spacecraft, high power geostationary orbit spacecraft and low power geostationary orbit spacecraft.

11. The spacecraft according to claim 1 wherein the spacecraft is configured to be mounted in a three spacecraft stack operable to be mounted in a single launch fairing.

12. A three-axis geostationary orbit spacecraft comprising:
a spacecraft body being rectangular shape and including first and second opposing radiator/equipment panels, first and second opposing mounting panels, an earth deck and a zenith deck, wherein the first and second radiator/equipment panels face a north/south X-direction relative to the Earth when the spacecraft is on orbit, the first and second mounting panels face an east/west Z-direction relative to the Earth when the spacecraft is on orbit, the earth deck faces the Earth when the spacecraft is on orbit, and the zenith deck faces away from the Earth when the spacecraft is on orbit;
a first solar panel mounted to the first radiator/equipment panel and extending therefrom and a second solar panel mounted to the second radiator/equipment panel and extending therefrom;
a plurality of phased arrays mounted to the earth deck;
a plurality of cross-link antennas mounted to the earth deck; and
a mounting cylinder extending through the spacecraft body and out of the first and second mounting panels, wherein the mounting cylinder includes a mounting flange at each end of the cylinder that are operable to be mounted to a mounting flange of a mounting cylinder of an adjacent spacecraft.

13. The spacecraft according to claim 12 wherein the plurality of phased arrays include a downlink phased array and an uplink phased array.

14. The spacecraft according to claim 12 wherein the plurality of plurality of phased arrays include at least one gimbal dish antenna.

15. The spacecraft according to claim 12 further comprising at least one antenna mounted to the zenith deck.

16. The spacecraft according to claim 12 further comprising one or more con-focal reflectors mounted to one or both of the earth deck and the zenith deck.

17. The spacecraft according to claim 12 wherein the spacecraft is selected from the group consisting of medium power geostationary orbit spacecraft, high power geostationary orbit spacecraft and low power geostationary orbit spacecraft.

18. A three-axis spacecraft comprising a spacecraft body including first and second opposing mounting panels that face an east and west direction relative to the Earth when the spacecraft is on orbit, an earth deck that faces the Earth when the spacecraft is on orbit and a zenith deck that faces away from the Earth when the spacecraft is on orbit, said spacecraft further comprising a mounting cylinder extending through the spacecraft body and out of the first and second opposing mounting panels.

19. The spacecraft according to claim 18 further comprising a plurality of antennas mounted to the earth deck that include at least one phased array.

20. The spacecraft according to claim 18 further comprising at least one antenna mounted to the zenith deck.

Assignees

• Northrop Grumman Systems Corp

Inventors

• Cherrette Alan R

Classifications

• B64G1/643

  for arranging multiple satellites in a single launcher · CPC title

• H01Q19/13

  the primary radiating source being a single radiating element, e.g. a dipole, a slot, a waveguide termination (H01Q19/15 takes precedence) · CPC title

• H01Q19/19

  comprising one main concave reflecting surface associated with an auxiliary reflecting surface · CPC title

• B64G1/64

  Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements · CPC title

• H01Q15/16

  curved in two dimensions [2D], e.g. paraboloidal · CPC title