Propulsion apparatus, flying body and propulsion method

Patent metadata

Field	Value
Publication number	US-12208906-B2
Application number	US-202117628301-A
Country	US
Kind code	B2
Filing date	Feb 3, 2021
Priority date	Feb 13, 2020
Publication date	Jan 28, 2025
Grant date	Jan 28, 2025

Abstract

A propulsion apparatus is provided with a gas generator and a plurality of thrusters. The gas generator generates combustion gas when a flying body satisfies an emergency condition. Herein, the plurality of thrusters output the combustion gas downward. In addition, when viewed from a direction of travel of the flying body, the plurality of thrusters may overlap the gas generator. Furthermore, the plurality of thrusters may control an attitude of the flying body. In addition, the plurality of thrusters may reduce outputs of the combustion gas to a first output based on a landing of at least a part of the flying body.

First claim

The invention claimed is:

1. A propulsion apparatus for a flying body, comprising:
a processor;
a gas generator configured to generate combustion gas;
a measuring device to generated status information of the flying body; and
a plurality of thrusters configured to output the combustion gas downward,
wherein the processor is configured to receive the status information of the flying body from the measuring device; based upon the status information, predict the flying body is to land in an area; determine whether at least one part of the flying body satisfies an emergency condition, determine the emergency condition is the at least one part of the flying body is predicted to land in the area, to cause the gas generator to generate the combustion gas upon determining that the at least one part of the flying body satisfies the emergency condition, and control the plurality of thrusters so that the at least one part of the flying body lands outside the area;
wherein the processor is further configured to determine whether the at least one part of the flying body is landed, to reduce an output of the combustion gas to a first output by which the flying body does not rise upon determining that the at least one part of the flying body is landed, and to cause the gas generator to continue outputting the combustion gas at the first output after the at least one part of the flying body is landed, and
wherein the processor is further configured to control outputs of the thrusters based on an altitude and a speed of the flying body.

2. The propulsion apparatus according to claim 1 ,
wherein the plurality of thrusters is further configured to overlap the gas generator when viewed from a direction of travel of the at least one part of the flying body.

3. The propulsion apparatus according to claim 1 ,
wherein the plurality of thrusters is further configured to control an attitude of the flying body.

4. The propulsion apparatus according to claim 1 ,
wherein the first output is determined based on a weight of the at least one part of the flying body.

5. The propulsion apparatus according to claim 1 ,
wherein a thrust of the plurality of thrusters at the first output is less than or equal to a weight of the at least one part of the flying body.

6. The propulsion apparatus according to claim 1 ,
wherein the plurality of thrusters is further configured to carry on outputting the combustion gas at the first output after the at least one part of the flying body is landed until fuel of the gas generator runs out.

7. The propulsion apparatus according to claim 1 ,
wherein the processor is configured to determine whether the emergency condition is satisfied based on an altitude of the at least one part of the flying body.

8. The propulsion apparatus according to claim 1 ,
wherein the processor is configured to determine whether the emergency condition is satisfied based on an expected fall position of the at least one part of the flying body.

9. A flying body comprising the propulsion apparatus according to claim 1 .

10. The flying body according to claim 9 , further comprising:
a booster to which the propulsion apparatus is attached; and
a payload attached in a direction of travel of the booster,
wherein the booster is configured to separate from the payload during a flight.

11. The flying body according to claim 10 ,
wherein the propulsion apparatus is provided at a location where the booster separates from the payload.

12. The flying body according to claim 9 , further comprising:
wheels configured to drive on a road.

13. The flying body according to claim 12 , further comprising:
an ordinary propulsion device different from the propulsion apparatus; and
a fuel supply device configured to supply fuel to the ordinary propulsion device,
wherein the fuel supply device is further configured to supply the fuel to the gas generator,
wherein the gas generator is further configured to:
store oxidizer;
add the oxidizer to the fuel supplied from the fuel supply device; and
combust the fuel added with the oxidizer.

14. A propulsion apparatus for a flying body, comprising:
a processor;
a gas generator configured to generate combustion gas;
a measuring device to generated status information of the flying body; and
a plurality of thrusters configured to output the combustion gas downward,
wherein the processor is configured to receive the status information of the flying body from the measuring device; based upon the status information, predict the flying body is to land in an area; determine whether at least one part of the flying body satisfies an emergency condition, determine the emergency condition is the at least one part of the flying body is predicted to land in the area, to cause the gas generator to generate the combustion gas upon determining that the at least one part of the flying body satisfies the emergency condition, and control the plurality of thrusters so that the at least one part of the flying body lands outside the area;
wherein the processor is further configured to determine whether the at least one part of the flying body is landed, to reduce an output of the combustion gas to a first output by which the flying body does not rise upon determining that the at least one part of the flying body is landed, and to cause the gas generator to continue outputting the combustion gas at the first output after the at least one part of the flying body is landed, and
wherein the processor is further configured to control outputs of the thrusters based on an altitude and a speed of the flying body.

Assignees

• Mitsubishi Heavy Ind Ltd
• Mitsubish Heavy Ind Ltd

Inventors

• Eguchi Masayuki
• Fujita Toshiharu
• Okumura Yukihiro

Classifications

• B64G1/401

  Liquid propellant rocket engines (Ion or plasma engines B64G1/413; Arcjets and other resistojets B64G1/415) · CPC title

• B64G1/244

  Spacecraft control systems · CPC title

• B64G1/002

  Launch systems · CPC title

• F02K9/566

  elements and safety devices, e.g. pressure relief valves · CPC title

• F02K9/56

  Control · CPC title