US3534686A - Payload/burned-out motor case separation system - Google Patents

Payload/burned-out motor case separation system Download PDF

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US3534686A
US3534686A US765123A US3534686DA US3534686A US 3534686 A US3534686 A US 3534686A US 765123 A US765123 A US 765123A US 3534686D A US3534686D A US 3534686DA US 3534686 A US3534686 A US 3534686A
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payload
motor case
separation
separation system
retrorockets
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Nathan D Watson
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National Aeronautics and Space Administration NASA
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64GCOSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00Cosmonautic vehicles
    • B64G1/22Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/641Interstage or payload connectors
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42BEXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64GCOSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00Cosmonautic vehicles
    • B64G1/22Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/641Interstage or payload connectors
    • B64G1/642Clamps, e.g. Marman clamps

Definitions

  • Patented Get. 20 1970 3,534,686
  • This invention relates to a payload separation system, and more particularly to a system for separating a payload from a spent rocket case prior to reentry of the payload into the atmosphere.
  • Another technique utilized for separating the last-stage motor case from the payload is that of a despin technique which also moves the spent motor case out of the path of the payload.
  • These devices have functioned satisfactorily to a degree; however, is not always as quick and clean as may be desired.
  • the requirement for despinning the spent motor case often requires the need for a spin table between the payload and spent motor case resulting in additional structure, expense and questionable reliability.
  • the present invention overcomes the above difficulties by providing a technique wherein retrorockets are used to accomplish separation.
  • the present invention eliminates many of the prior art difficulties by timing the firing sequence of the retrorockets.
  • the first retrorocket is tired causing the spent motor case to move away from the payload and also to cant or assume a position at an angle with respect to the line-of-flight of the payload.
  • an opposed retrorocket is fired.
  • Yet another object of the invention is to provide a technique for separating a spent rocket motor case and a payload wherein it is not necessary to despin the motor case prior to separation.
  • a further object of the invention is to provide separation of a spent rocket motor case and a payload wherein the components utilized for separation are simple to manufacture, operate and maintain.
  • An additional object of the invention is to provide a separation technique which is highly reliable and will result in the spent rocket motor case being translated out of the flightpath of the payload as well as separated from the payload.
  • Still another object of the invention is to provide an arrangement for separating a payload from a spent motor case wherein the initial separation of the components initiates the separation system.
  • FIG. I is an elevational view showing the sequence of payload and spent motor case separation
  • FIG. 2 is an elevational view showing the connected payload and motor case and the location of the separation system components
  • FIG. 3 is a schematic diagram of a circuit utilized to energize the separation system.
  • FIG. 2 shows the joined payload and spent motor case as it might appear just prior to entering the atmosphere. These components being designated generally by the reference numeral ten.
  • the payload I2 may take various shapes and forms, the particular payload shown being that ofone utilized to test the properties of an ablation material which has possible use on a reentry capsule.
  • the payload I2 is joined to a motor case 16 by a clamping mechanism 14.
  • the clamping mechanism 14 is of the explosive bolt type, known in the prior art as a Marmon Band clamp. This type clamp utilizes an explosive bolt to release the clamping arrangement, and usually has some type of compressed spring associated therewith. the energy of which causes initial separation between the payload and the body being separated therefrom.
  • the motor case 16 is a conventional solid propellant type, having an adapter I8 attached to the lower portion thereof in the usual manner.
  • retrorockets 28 and 30 Affixed to the adapter 18 are retrorockets 28 and 30.
  • the retrorockets are of the squib-actuated solid propellant type and are located directly opposite each other on the adapter. It has been found by experimentation that the general location of the retrorockets as shown in FIG. 2 is advantageous to the separation procedure. However, it should be understood that the retrorockets may assume other positions and accomplish the purpose of the invention.
  • FIG. 3 shows a circuit which is utilized to energize the retrorockets to accomplish separation of the payload l2 and the motor case 16.
  • the separation switch 20 is positioned in series with a battery 22, the separation switch 20 being designed so that it is closed upon separation of the payload from the motor case. Closing of the separation switch 20 also results in the simultaneous closing of switches 24 and 26 which are in parallel with the battery and in series with the retrorockets 28 and 30, respectively.
  • the particular switches utilized are of the pyrotechnic type which are selected to burn at different time intervals upon being closed.
  • the switch 24 can be set to burn immediately and ignite the first retrorocket 28, and the other switch 26 is selected to burn a fraction of a second prior to igniting the second retrorocket.
  • the switches 24 and 26 could be of some timedelay type to allow sequential burning of the retrorockets thereby accomplishing the purpose of the invention.
  • the particular payload utilized with this separation technique is normally of the type which is launched into space and then directed back toward the atmosphere and accelerated as it returns toward the atmosphere. This is the reason why the motor case is still usually attached to the payload just prior to its reentry into the atmosphere.
  • the purpose of obtaining as high a velocity as possible for the payload is also the reason for separating the motor case from the payload.
  • the explosive bolt mechanism of the Marmon Band is actuated which allows the clamping mechanism to separate. Separation of the components of the clamp is assured by the spring mechanism under compression which exerts a pressure against the payload and motor case causing initial separation. This closes the separation switch 20 which places switches 24 and 26 across the battery thereby closing the switches.
  • Switch 24 associated with the first retrorocket 28 is set so that it immediately ignites the first retrorocket. Since the retrorocket 28 is placed on one side of the adapter nozzle 18, it will apply an unbalanced force to the motor case causing it to cant or assume an angle with respect to the normal flightpath of the payload as shown in FIG. 1.
  • the second switch 26 after being closed a time interval, for example, 0.8 seconds, then allows ignition of the second retromotor 30. Sufficient fuel is provided in the first rocket motor 28 such that both retromotors 28 and 30 burn simultaneously. A balanced force is now applied to the motor case 16. and the case is thereby translated out of the path of the payload.
  • the invention provides an arrangement for rapid and clean separation of a payload from a burned-out rocket motor case.
  • the spent motor case is not only separated but moved out of the path of the payload, thus preventing any possibility of the motor case overrunning and colliding with the payload.
  • the separation system has few component parts resulting in a device economical to manufacture and maintain. Also, the minimum number of components greatly enhances the reliability of the separation technique since there are few pieces of mechanism subject to failure.
  • the system is also readily adaptable to various size payloads and motor cases making a particularly versatile arrangement. Since separation is effectively accomplished without the necessity of despinning the bumed-out rocket motor case, the structure normally required for despinning is eliminated.
  • a payload rocket motor separation system for a spin-stabilized vehicle comprising:
  • clamping means for connecting said payload means and rocket motor means
  • a second retro propulsion means attached to said rocket motor means actuated subsequent to said first retro propulsion means whereby said rocket motor means is separated and laterally displaced from said payload means.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)

Description

Waited States Patent Nathan D. Watson Hampton, Virginia 765,123
Oct. 4, 1968 Oct. 20, 1970 Inventor Appl. No. Filed Patented Assignee the United States of America as represented by the Administrator of the National Aeronautics and Space Administration PAYLOAD/BURNED-OUT MOTOR CASE SEPARATION SYSTEM 8 Claims, 3 Drawing Figs.
[1.8. CI 102/495 Int. Cl F02k 9/06 Field of Search 102/494,
49.5; 244/I(S.S.)
[56] References Cited UNITED STATES PATENTS 3,185,096 5/1965 Daudelin l02/49.4 3,384,016 5/1968 Blanchard 102/495 3,431,854 3/1969 Rabenhorst [OZ/49.4
Primary Examiner Verlin R. Pendegrass Att0rneysI-Ioward J. Osborn and G. T. McCoy ABSTRACT: A payload separation system wherein a Marmon Band clamp separates a spent motor case from the payload. A retrorocket fixed to the motor case is fired to cant the motor case. Another opposed retrorocket is ignited while the first one is still burning and together they move the spent motor case out of the path of the payload.
Patented Get. 20, 1970 3,534,686
MG. 2 I J' [if i I8 f INVENTOR.
NATHAN D. WAT
BY 2 S 31 ATTORNEYS PAYLOAD/BURNED-OUT MOTOR CASE SEPARATION SYSTEM The invention described herein was made by an employee of the US Government and may be manufactured and used by or for the Government for governmental purposes without the payment of any royalties thereon or therefor.
This invention relates to a payload separation system, and more particularly to a system for separating a payload from a spent rocket case prior to reentry of the payload into the atmosphere.
Various prior art techniques have been used in attempting to provide a clean and continued separation of a reentering payload from the last-stage motor case. One such technique is the use of retrorockets wherein the last-stage motor is separated in a direct line from the payload. Although this ar rangement is successful to a degree, the mere separation of the devices is not always satisfactory because the payload breaks a trail, so to speak, resulting in a last-stage motor case encountering very little resistance and therefore at times actually catching up with and colliding with the payload.
Another technique utilized for separating the last-stage motor case from the payload is that of a despin technique which also moves the spent motor case out of the path of the payload. These devices have functioned satisfactorily to a degree; however, is not always as quick and clean as may be desired. Furthermore, the requirement for despinning the spent motor case often requires the need for a spin table between the payload and spent motor case resulting in additional structure, expense and questionable reliability.
The present invention overcomes the above difficulties by providing a technique wherein retrorockets are used to accomplish separation. The present invention, however, eliminates many of the prior art difficulties by timing the firing sequence of the retrorockets. The first retrorocket is tired causing the spent motor case to move away from the payload and also to cant or assume a position at an angle with respect to the line-of-flight of the payload. While the first retrorocket is still firing, and at an optimum calculated time, an opposed retrorocket is fired. The two retrorockets burning together, then translate the spent motor case out of the path of the payload assuring a clean and continued separation of the components.
It is therefore an object of the invention to provide a technique for separating a payload from a spent rocket case with the use of sequentially timed retrorockets.
Yet another object of the invention is to provide a technique for separating a spent rocket motor case and a payload wherein it is not necessary to despin the motor case prior to separation.
A further object of the invention is to provide separation of a spent rocket motor case and a payload wherein the components utilized for separation are simple to manufacture, operate and maintain.
An additional object of the invention is to provide a separation technique which is highly reliable and will result in the spent rocket motor case being translated out of the flightpath of the payload as well as separated from the payload.
Still another object of the invention is to provide an arrangement for separating a payload from a spent motor case wherein the initial separation of the components initiates the separation system.
These and other objects and advantages of the invention will become more apparent upon reading the specification taken in conjunction with the accompanying drawings.
In the drawings:
FIG. I is an elevational view showing the sequence of payload and spent motor case separation;
FIG. 2 is an elevational view showing the connected payload and motor case and the location of the separation system components; and
FIG. 3 is a schematic diagram of a circuit utilized to energize the separation system.
Referring now more specifically to the details of the invention, FIG. 2 shows the joined payload and spent motor case as it might appear just prior to entering the atmosphere. these components being designated generally by the reference numeral ten.
The payload I2 may take various shapes and forms, the particular payload shown being that ofone utilized to test the properties of an ablation material which has possible use on a reentry capsule.
The payload I2 is joined to a motor case 16 by a clamping mechanism 14. The clamping mechanism 14 is of the explosive bolt type, known in the prior art as a Marmon Band clamp. This type clamp utilizes an explosive bolt to release the clamping arrangement, and usually has some type of compressed spring associated therewith. the energy of which causes initial separation between the payload and the body being separated therefrom. The motor case 16 is a conventional solid propellant type, having an adapter I8 attached to the lower portion thereof in the usual manner.
Affixed to the adapter 18 are retrorockets 28 and 30. The retrorockets are of the squib-actuated solid propellant type and are located directly opposite each other on the adapter. It has been found by experimentation that the general location of the retrorockets as shown in FIG. 2 is advantageous to the separation procedure. However, it should be understood that the retrorockets may assume other positions and accomplish the purpose of the invention.
FIG. 3 shows a circuit which is utilized to energize the retrorockets to accomplish separation of the payload l2 and the motor case 16. The separation switch 20 is positioned in series with a battery 22, the separation switch 20 being designed so that it is closed upon separation of the payload from the motor case. Closing of the separation switch 20 also results in the simultaneous closing of switches 24 and 26 which are in parallel with the battery and in series with the retrorockets 28 and 30, respectively. The particular switches utilized are of the pyrotechnic type which are selected to burn at different time intervals upon being closed. Thus, the switch 24 can be set to burn immediately and ignite the first retrorocket 28, and the other switch 26 is selected to burn a fraction of a second prior to igniting the second retrorocket. Obviously, the switches 24 and 26 could be of some timedelay type to allow sequential burning of the retrorockets thereby accomplishing the purpose of the invention.
OPERATION From the above description of the separation system, it is believed that the operation thereof is readily apparent. However, the details will be explained to assure ample understandmg.
The particular payload utilized with this separation technique is normally of the type which is launched into space and then directed back toward the atmosphere and accelerated as it returns toward the atmosphere. This is the reason why the motor case is still usually attached to the payload just prior to its reentry into the atmosphere. The purpose of obtaining as high a velocity as possible for the payload is also the reason for separating the motor case from the payload.
As the payload enters the atmosphere, the explosive bolt mechanism of the Marmon Band is actuated which allows the clamping mechanism to separate. Separation of the components of the clamp is assured by the spring mechanism under compression which exerts a pressure against the payload and motor case causing initial separation. This closes the separation switch 20 which places switches 24 and 26 across the battery thereby closing the switches. Switch 24 associated with the first retrorocket 28 is set so that it immediately ignites the first retrorocket. Since the retrorocket 28 is placed on one side of the adapter nozzle 18, it will apply an unbalanced force to the motor case causing it to cant or assume an angle with respect to the normal flightpath of the payload as shown in FIG. 1. The second switch 26 after being closed a time interval, for example, 0.8 seconds, then allows ignition of the second retromotor 30. Sufficient fuel is provided in the first rocket motor 28 such that both retromotors 28 and 30 burn simultaneously. A balanced force is now applied to the motor case 16. and the case is thereby translated out of the path of the payload.
it should be apparent that different size retromotors, as well as different time sequences of firing will be necessary depending on the size of the payload and motor case, the velocity of the components and other factors. By experimentation it has been shown that the transverse and longitudinal separation distances versus time can be readily calculated on commercially available computing equipment enabling proper setting for retrorocket firing.
From the above description, it is apparent that the invention provides an arrangement for rapid and clean separation of a payload from a burned-out rocket motor case. By using retrorockets which are fired at different intervals than simultaneously, the spent motor case is not only separated but moved out of the path of the payload, thus preventing any possibility of the motor case overrunning and colliding with the payload. The separation system has few component parts resulting in a device economical to manufacture and maintain. Also, the minimum number of components greatly enhances the reliability of the separation technique since there are few pieces of mechanism subject to failure. The system is also readily adaptable to various size payloads and motor cases making a particularly versatile arrangement. Since separation is effectively accomplished without the necessity of despinning the bumed-out rocket motor case, the structure normally required for despinning is eliminated.
While a preferred embodiment of this invention has been described, it is understood that modifications and improvements can be made thereto. Such of these modifications and improvements as incorporate the principles of this invention are to be considered in the hereinafter appended claims unless these claims by their very language expressly state otherwise.
lelaim:
1. A payload rocket motor separation system for a spin-stabilized vehicle comprising:
payload means;
rocket motor means;
clamping means for connecting said payload means and rocket motor means;
means for releasing said clamping means at a selected time;
a first retro propulsion means attached to said rocket motor means activated upon release of said clamping means; and
a second retro propulsion means attached to said rocket motor means actuated subsequent to said first retro propulsion means whereby said rocket motor means is separated and laterally displaced from said payload means.
2. A payload rocket motor separation system for a spin-stabilized vehicle as in claim 1 wherein said first and second retro propulsion means are solid propellant retrorockets.
3. A payload rocket motor separation system for a spin-stabilized vehicle as in claim 2 wherein said first and second retrorockets are secured to the adapter of the rocket motor means; said first and second retrorockets being positioned on opposite sides of said rocket motor adapter.
4. A payload rocket motor separation system for a spin-stabilized vehicle as in claim 1 wherein a separation switch is located between said rocket motor means and payload means; first and second delay switches closed by the operation of said separation switch, said separation switch being closed by release of said clamping means.
5. A payload rocket motor separation system for a spin-stabilized vehicle as in claim 4 wherein said first delay switch initiates said first retro propulsion means and said second delay switch initiates said second retro propulsion means.
6. A payload rocket motor separation system for s spin-stabilized vehicle as in claim 1 wherein said first retro propulsion means burns while said second retro propulsion means IS initiated and operative.
7. A payload rocket motor separation system for a spin-stabilized vehicle as in claim 1 wherein said first and second retro propulsion means are activated while said payload and rocket means are spinning.
8. A payload rocket motor separation system for a spin-stabilized vehicle as in claim 1 wherein said first retro propulsion means upon initiation tips said rocket motor means case to a new attitude; and said first and second retro propulsion means move the rocket motor means back and to the side of said payload means.
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Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3934512A (en) * 1973-12-03 1976-01-27 Kazuhide Adachi Liquid fuel multistage rocket
US4137848A (en) * 1975-11-05 1979-02-06 The United States Of America As Represented By The Secretary Of The Navy Rocket engine mount
US4408536A (en) * 1977-06-30 1983-10-11 The United States Of America As Represented By The Secretary Of The Navy Method of re-entry body separation and ejection
FR2649667A1 (en) * 1989-07-17 1991-01-18 Centre Nat Etd Spatiales METHOD FOR LAUNCHING IN THE SPACE OF A CAPSULE AND MEANS FOR LAUNCHING THE SAME
EP0413670A1 (en) * 1989-08-17 1991-02-20 Aktiebolaget Bofors Method for separating warheads
FR2729117A1 (en) * 1995-01-10 1996-07-12 Aerospatiale Missile guidance procedure
US5927653A (en) * 1996-04-17 1999-07-27 Kistler Aerospace Corporation Two-stage reusable earth-to-orbit aerospace vehicle and transport system
US6076771A (en) * 1998-02-25 2000-06-20 Kistler Aerospace Corporation System and method for controlling a re-entry vehicle
US6158693A (en) * 1998-02-25 2000-12-12 Kistler Aerospace Corporation Recoverable booster stage and recovery method
US20040253399A1 (en) * 2002-08-23 2004-12-16 M&Q Plastic Products, Inc. Cook and chill casing
US20070063107A1 (en) * 2005-09-19 2007-03-22 Kistler Aerospace Corporation Reusable orbital vehicle with interchangeable cargo modules
CN102139766A (en) * 2010-10-28 2011-08-03 中国科学院力学研究所 Method for obtaining design attack angle for reentry flight of suborbital vehicle
CN102139767A (en) * 2010-10-28 2011-08-03 中国科学院力学研究所 Cross adjustment method for reentry flight process of suborbital vehicle
CN102139768A (en) * 2010-10-28 2011-08-03 中国科学院力学研究所 Reentry flight attack angle guiding method of sub-orbital vehicle
RU2517993C1 (en) * 2012-11-07 2014-06-10 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Омский государственный технический университет" Method of rocket engine thrust development
RU2518918C2 (en) * 2012-08-22 2014-06-10 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Омский государственный технический университет" Withdrawal of carrier rocket stage separated part from payload orbit and device to this end
US20140158830A1 (en) * 2011-07-18 2014-06-12 D-Or-Bit S.R.L. Device for moving or removing artificial satellites
RU2522536C1 (en) * 2012-12-07 2014-07-20 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Омский государственный технический университет" Method of rocket in-tank liquid-propellant gasification and device to this end
US20140263841A1 (en) * 2013-03-15 2014-09-18 Blue Origin, Llc Launch vehicles with ring-shaped external elements, and associated systems and methods
US9580191B2 (en) 2009-02-24 2017-02-28 Blue Origin, Llc Control surfaces for use with high speed vehicles, and associated systems and methods
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Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3934512A (en) * 1973-12-03 1976-01-27 Kazuhide Adachi Liquid fuel multistage rocket
US4137848A (en) * 1975-11-05 1979-02-06 The United States Of America As Represented By The Secretary Of The Navy Rocket engine mount
US4408536A (en) * 1977-06-30 1983-10-11 The United States Of America As Represented By The Secretary Of The Navy Method of re-entry body separation and ejection
FR2649667A1 (en) * 1989-07-17 1991-01-18 Centre Nat Etd Spatiales METHOD FOR LAUNCHING IN THE SPACE OF A CAPSULE AND MEANS FOR LAUNCHING THE SAME
EP0409711A1 (en) * 1989-07-17 1991-01-23 Centre National D'etudes Spatiales Process to launch a capsule in space and launching means
EP0413670A1 (en) * 1989-08-17 1991-02-20 Aktiebolaget Bofors Method for separating warheads
US6142424A (en) * 1995-01-10 2000-11-07 Aerospatiale Societe Nationale Industrielle Method of steering a vehicle and vehicle allowing implementation of the method
FR2729117A1 (en) * 1995-01-10 1996-07-12 Aerospatiale Missile guidance procedure
US5927653A (en) * 1996-04-17 1999-07-27 Kistler Aerospace Corporation Two-stage reusable earth-to-orbit aerospace vehicle and transport system
US6076771A (en) * 1998-02-25 2000-06-20 Kistler Aerospace Corporation System and method for controlling a re-entry vehicle
US6158693A (en) * 1998-02-25 2000-12-12 Kistler Aerospace Corporation Recoverable booster stage and recovery method
US20040253399A1 (en) * 2002-08-23 2004-12-16 M&Q Plastic Products, Inc. Cook and chill casing
US20070063107A1 (en) * 2005-09-19 2007-03-22 Kistler Aerospace Corporation Reusable orbital vehicle with interchangeable cargo modules
US7198233B1 (en) * 2005-09-19 2007-04-03 Kistler Aerospace Corporation Reusable orbital vehicle with interchangeable cargo modules
US11649073B2 (en) 2009-02-24 2023-05-16 Blue Origin, Llc Control surfaces for use with high speed vehicles, and associated systems and methods
US10518911B2 (en) 2009-02-24 2019-12-31 Blue Origin, Llc Control surfaces for use with high speed vehicles, and associated systems and methods
US9580191B2 (en) 2009-02-24 2017-02-28 Blue Origin, Llc Control surfaces for use with high speed vehicles, and associated systems and methods
CN102139768A (en) * 2010-10-28 2011-08-03 中国科学院力学研究所 Reentry flight attack angle guiding method of sub-orbital vehicle
CN102139766B (en) * 2010-10-28 2013-01-23 中国科学院力学研究所 Method for obtaining design attack angle for reentry flight of suborbital vehicle
CN102139767B (en) * 2010-10-28 2013-04-10 中国科学院力学研究所 Cross adjustment method for reentry flight process of suborbital vehicle
CN102139766A (en) * 2010-10-28 2011-08-03 中国科学院力学研究所 Method for obtaining design attack angle for reentry flight of suborbital vehicle
CN102139768B (en) * 2010-10-28 2013-04-10 中国科学院力学研究所 Reentry flight attack angle guiding method of sub-orbital vehicle
CN102139767A (en) * 2010-10-28 2011-08-03 中国科学院力学研究所 Cross adjustment method for reentry flight process of suborbital vehicle
US20140158830A1 (en) * 2011-07-18 2014-06-12 D-Or-Bit S.R.L. Device for moving or removing artificial satellites
US9751643B2 (en) * 2011-07-18 2017-09-05 D-Orbit S.R.L. Device for moving or removing artificial satellites
RU2518918C2 (en) * 2012-08-22 2014-06-10 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Омский государственный технический университет" Withdrawal of carrier rocket stage separated part from payload orbit and device to this end
RU2517993C1 (en) * 2012-11-07 2014-06-10 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Омский государственный технический университет" Method of rocket engine thrust development
RU2522536C1 (en) * 2012-12-07 2014-07-20 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Омский государственный технический университет" Method of rocket in-tank liquid-propellant gasification and device to this end
US9487308B2 (en) * 2013-03-15 2016-11-08 Blue Origin, Llc Launch vehicles with ring-shaped external elements, and associated systems and methods
US20140263841A1 (en) * 2013-03-15 2014-09-18 Blue Origin, Llc Launch vehicles with ring-shaped external elements, and associated systems and methods
US10266282B2 (en) 2013-03-15 2019-04-23 Blue Origin, Llc Launch vehicles with ring-shaped external elements, and associated systems and methods
US10822122B2 (en) 2016-12-28 2020-11-03 Blue Origin, Llc Vertical landing systems for space vehicles and associated methods

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