GB2091194A - Apparatus for carrying out experiments under conditions of weightlessness - Google Patents
Apparatus for carrying out experiments under conditions of weightlessness Download PDFInfo
- Publication number
- GB2091194A GB2091194A GB8201033A GB8201033A GB2091194A GB 2091194 A GB2091194 A GB 2091194A GB 8201033 A GB8201033 A GB 8201033A GB 8201033 A GB8201033 A GB 8201033A GB 2091194 A GB2091194 A GB 2091194A
- Authority
- GB
- United Kingdom
- Prior art keywords
- unit
- devices
- experiments
- units
- operational unit
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 238000002474 experimental method Methods 0.000 title claims abstract description 38
- 238000003032 molecular docking Methods 0.000 claims abstract description 9
- 230000007246 mechanism Effects 0.000 claims abstract description 8
- 238000004891 communication Methods 0.000 claims abstract description 5
- 238000000034 method Methods 0.000 claims description 6
- 230000008878 coupling Effects 0.000 claims description 2
- 238000010168 coupling process Methods 0.000 claims description 2
- 238000005859 coupling reaction Methods 0.000 claims description 2
- 230000007774 longterm Effects 0.000 claims description 2
- 230000000295 complement effect Effects 0.000 abstract description 2
- 238000010438 heat treatment Methods 0.000 description 5
- 238000011160 research Methods 0.000 description 4
- 238000012360 testing method Methods 0.000 description 4
- 235000015842 Hesperis Nutrition 0.000 description 3
- 235000012633 Iberis amara Nutrition 0.000 description 3
- 239000013078 crystal Substances 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 230000008901 benefit Effects 0.000 description 1
- 230000031018 biological processes and functions Effects 0.000 description 1
- 239000000969 carrier Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010494 dissociation reaction Methods 0.000 description 1
- 230000005593 dissociations Effects 0.000 description 1
- 239000003814 drug Substances 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 238000004886 process control Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01L—CHEMICAL OR PHYSICAL LABORATORY APPARATUS FOR GENERAL USE
- B01L1/00—Enclosures; Chambers
- B01L1/52—Transportable laboratories; Field kits
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/223—Modular spacecraft systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/646—Docking or rendezvous systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/105—Space science
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/1078—Maintenance satellites
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/1085—Swarms and constellations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G4/00—Tools specially adapted for use in space
- B64G2004/005—Robotic manipulator systems for use in space
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Clinical Laboratory Science (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Manipulator (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
Apparatus for carrying out experiments in weightlessness in orbit around the earth comprises two units which can be coupled together. A first unit 1 is equipped as an operational unit for a lengthy period in orbit, i.e. it is equipped with sub systems known for current supply, position control, thermal economy, communications links and docking mechanisms as well as with special devices required in order to carry out the experiments, such as energy supply devices, control mechanisms and their related electronic units, measuring devices, manipulators, etc. The second unit 2 is a transportation unit and has containers and manipulators for receiving and delivering devices required in order to carry out the experiments, i.e. for handing them over to or taking charge of them from the operational unit. The second unit 2 also has drive and control devices required in order to control the operational unit and the complementary docking mechanisms required for docking with the operational unit. <IMAGE>
Description
SPECIFICATION
Apparatus for carrying out experiments under conditions of weightlessness
The invention relates to an apparatus suitable for carrying out basic experiments in weightlessness in an orbit around the earth such as those which have been carried out individually in so called space laboratories which have a crew of astronauts.
It is known that many processes which are of a physical, chemical or biological nature are different in conditions of weightlessness from the conditions prevailing at the earth's surface with its gravity. In the field of chemistry for example reactions are at least partially different when the reacting chemicals are not subjected to gravity which leads to dissociation, particularly when they have different densities.
The same is true of numerous physical processes.
Furthermore, in some cases it is known and in other cases it can be conjectured that biological processes have different requirements in conditions of weightlessness and therefore lead to different results.
This is why, in the past, few of these tests have been carried out in so called space laboratories occupied by astronauts or cosmonauts. In addition there have been experiments of this type forming the payload of rockets sent up to heights of several kilometres so that on their return to earth in free fall they were also subjected for a short time to conditions of weightlessness.
Whereas the first above-mentioned experiments in the so called space laboratories were exceptionally expensive, the experiments using rockets, which were inherently cheaper, only allowed for tests during very short periods of weightlessness.
In order to carry out these experiments in the future at a substantially lower cost, re usable spacecraft are currently being constructed as carriers for specially developed space laboratories which can be used to implement experiments which require fairly long periods of time under the supervision of scientists. Of course, these experiments are still relatively expensive particularly in the case of basic research which need not necessarily be under human supervision and which should be carried out over fairly long periods of time.
In addition, it is known to put into orbit specially equipped satellites with the aid of rockets which are not themselves re-usable, the devices on board the satellite being able to carry out their tasks from the satellite for long periods of time. In order to achieve this these satellites are provided with energy supply devices, devices for controlling their position, for communications links etc., these devices and arrangements allowing the satellites to remain operational for years. In the past these satellites have however only been able to carry out quite specialised individual tasks and were not used for basic research.
It is an object of the present invention to provide a device which can be put into orbit by space transportation systems currently under construction and which once there is in a position to carry out basic research experiments autonomously over lengthy periods. The experiment modules themselves are preferably returnable in orderto evaluate these experiments more exactly over the above the possibilities provided by telemetry.
In accordance with the present invention there is provided apparatus for carrying out experiments under conditions of weightlessness comprising two units which can be coupled together, one of which is equipped as an operational unit with subsystems which are required for long term stay in orbit and the other of which is equipped as a transportation unit with devices for transporting and supplying experimental modules to or receiving experimental modules from the operational unit, and control and docking means which are used to couple the transportation unit to the operational unit.
The subsystems may be for current supply, position control, thermal economy, communications links, docking mechanisms and/or specialised devices required in order to carry out the experiments.
The specialised devices may be energy supply devices, control mechanisms with related electronic units, measuring devices with electronic units and/or manipulators.
In a preferred arrangement the transportation unit has transportation containers and manipulators for delivering, receiving and taking charge of experimental modules to and from the operational unit. The transportation may also have one or more drive devices and control devices for controlling the operational unit and the complementary docking mechanisms required during docking of the units.
The transportation unit may provide the operational unit with any desired supplies while carrying out the experiments. It may also pass back from the operatio;.al unit test results which have already been obtained and, if necessary receive defective apparatus and return it to the earth's surface without the experiments being carried out in the operational unit having to be interrupted. Of course several transportation units can be used for a single operational unit.
Further in accordance with the present invention there is provided a method employing apparatus as defined above wherein the operational unit and the transportation unit are put into an earth orbit separately or jointly and are set up and manipulated therein.
A preferred embodiment of the present invention will now be described by way of example only with reference to the accompanying drawings, of which;
Figure 1 shows two parts of apparatus in accordance with the present invention;
Figure 2 shows the operational unit of the apparatus of Figure 1; and
Figure 3 shows the transportation unit of the apparatus of Figure 1.
Referring now to the drawings, in Figure 1 the operational unit 1 and the transportation unit 2 are shown schematically before the two units are coupled. The operational unit has two solar panels 3 and an antenna unit 6 which is known per se and which serves to supply energy and to provide communications links. A manipulator4which couples the two units is arranged on the transportation unit 2 and the centring means 5a of the transportation unit and 5b of the operational unit ensure accurate coupling.
The operational unit 1 (Figure 2) has the centring device 5b at the centre of its central tube or duct 15.
The special devices for different basic experiments are arranged all round this central tube 15. The chambers 8, for example, serve for crystal growing, chambers 9 for biological and medical experiments, and chamber 10 has a gradient heating system, while chamber 11 has an isothermal heating system.
The devices for transmitting and receiving information via the antenna 6 are designated as chamber 12, fuel tanks for supply to position control devices (not shown) are housed in chamber 13 and apparatus for tests at high temperatures can be arranged in chamber 14. Finally, the chamber housing batteries for energy supply are designated 7.
The transportation unit 2 provided for the operational unit 1 shown in Figure 2 is shown in Figure 3.
The centring device 5a is also arranged at the centre of the central tube or duct 1 5a in this case. A thrust unit may be provided in the region of the central tube. Since the operational unit 1 can be coupled to the transportation unit 2 with the aid of the manipulator 4 and the centring device 5a, 5b, distribution of the spaces for the individual experiment modules which have to betransported is obviously a mirror image of the arrangement of the operational unit 1.
Thus the chambers 8a serve to transport the experiment modules for experiments on crystal growth, chambers 9a serve for experiments from the field of biology and medicine, chamber 10a for experiments carried out in the gradient heating system 10 and chamber 11 a for experiments in the isothermal heating system 11. The control system for the manipulator 4 is designated 16, while electronic modules for process control of the heating systems may be arranged in chamber 17 for example.
In order to utilise the apparatus the two units of the apparatus are put into their prescribed orbit and set up there with the aid of a space transportation system which is known perse. In the first instance the manipulator which is provided on board the space transportation system is used. The two units of the apparatus may be already coupled together when loading the apparatus on board the space transportation system, however they may also be transported individually into orbit and then be
coupled with the aid of the means provided on board the operational unit and on board the transportation
unit. The space transportation system can then
return to the earth's surface independently of the
apparatus.Once the period of time provided for the
experiments has come to an end, the experiment
modules in the transportation unit are collected
again by the spacecraft and replaced with the aid of a
further transportation unit which is equipped with
new experiments without the operational unit also
having to be brough back to the earth's surface.
Actual evaluation of the basic experiments can then
be undertaken on the surface of the earth. The mass
which has to be transported using this apparatus is
very much smaller in any case than is usual in the
case of methods currently used and therefore there
is also a corresponding reduction in both the mass and the costs involved.
The above-described apparatus has the advantage over previously known plans that a substantial part of the apparatus i.e. the operational unit, only has to be brought back out of its orbit on to the earth, if at all, at very large intervals of time. By using a separate transportation unit for the actual experiment modules and for the special devices required for the experiments it is possible to carry out basic research experiments at substantially lower cost, in terms of the loads which have to be put into orbit.
These experiments last for different periods of time and therefore they can be carried out much more cheaply using the apparatus. In addition, subsystems which have been known for a long time and which are designed for the operational unit are used and serve to control the position of the unit and supply it with energy. The systems required for linking the two units are already known and do not need any specific development.
Claims (11)
1. Apparatus for carrying out experiments under conditions of weightlessness comprising two units which can be coupled together, one of which is equipped as an operational unit with subsystems which are required for long term stay in orbit and the other of which is equipped as a transportation unit with devices for transporting and supplying experimental modules to or receiving experimental modules from the operational unit, and control and docking means which are used to couple the transportation unit to the operational unit.
2. Apparatus according to claim 1, wherein said subsystems are for current supply, position control, thermal economy, communications links, docking mechanisms and/or specialised device required in order to carry out the experiments.
3. Apparatus according to claim 2 wherein said specialised devices are energy supply devices, control mechanisms with related electronic units, measuring devices with electronic units and/or manipulators.
4. Apparatus according to any preceding claim, wherein the transportation unit is provided with drive means.
5. Apparatus according to any preceding claim wherein the two units have at least substantially equal outer dimensions.
6. Apparatus according to any preceding claim wherein the subsystems and devices in each unit are arranged around a central duct which occupies a central region ofthe respective unit.
7. Apparatus according to claim 5 wherein a centring device for coupling the units is arranged in the central duct.
8. Apparatus according to any preceding claim, wherein a thrust unit is arranged in the region of the
central duct.
9. A method employing apparatus according to
any preceding claim, wherein the operational unit
and the transportation unit are put into an earth orbit
separately or jointly and are set up and manipulated there.
10. Apparatus substantially as herein described with reference to the accompanying drawings.
11. A method of carrying out experiments in conditions of weightlessness substantially as herein described with reference to the accompanying drawings.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19813101368 DE3101368A1 (en) | 1981-01-17 | 1981-01-17 | "DEVICE FOR CARRYING OUT BASIC EXPERIMENTS UNDER EFFECTIVENESS IN AN EARTH ORBIT" |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB2091194A true GB2091194A (en) | 1982-07-28 |
Family
ID=6122809
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB8201033A Withdrawn GB2091194A (en) | 1981-01-17 | 1982-01-14 | Apparatus for carrying out experiments under conditions of weightlessness |
Country Status (5)
| Country | Link |
|---|---|
| JP (1) | JPS57122000A (en) |
| DE (1) | DE3101368A1 (en) |
| FR (1) | FR2498156A1 (en) |
| GB (1) | GB2091194A (en) |
| IT (1) | IT1139789B (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0134288A1 (en) * | 1983-09-03 | 1985-03-20 | ERNO Raumfahrttechnik Gesellschaft mit beschränkter Haftung | Satellite system with variable configuration |
| FR2593466A1 (en) * | 1985-10-30 | 1987-07-31 | Rca Corp | SPACE VEHICLE STRUCTURE FOR ASSEMBLY AND TROUBLESHOOTING IN ORBIT |
| US4834325A (en) * | 1985-03-20 | 1989-05-30 | Space Industries, Inc. | Modular spacecraft system |
| US4865514A (en) * | 1986-10-03 | 1989-09-12 | Hitachi, Ltd. | Manipulator system with small arm removably attachable at points along large arm |
| US4880187A (en) * | 1986-01-16 | 1989-11-14 | Trw Inc. | Multipurpose modular spacecraft |
| FR2636040A1 (en) * | 1988-09-06 | 1990-03-09 | Matra | Space vehicle for a mission in microgravity and method of experimentation using such a vehicle |
| EP0541052A1 (en) * | 1991-11-05 | 1993-05-12 | Hitachi, Ltd. | Spacecraft system |
| US5429328A (en) * | 1992-11-16 | 1995-07-04 | Environmental Research Institute Of Michigan | Spacecraft payload exchange system |
| EP0826596A1 (en) * | 1996-08-29 | 1998-03-04 | Space Systems/Loral, Inc. | Space platform assembly for attachment to a space station |
| US5950965A (en) * | 1997-07-17 | 1999-09-14 | Lockheed Martin Corporation | Split shell spacecraft |
| US6149104A (en) * | 1998-04-01 | 2000-11-21 | Trw Inc. | Structural layout for spacecraft including specialized compartment configuration |
| US6193193B1 (en) * | 1998-04-01 | 2001-02-27 | Trw Inc. | Evolvable propulsion module |
| CN105035360A (en) * | 2015-07-31 | 2015-11-11 | 上海卫星工程研究所 | Cabin-segmentation type separable platform configuration based on four-point connection |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3940041C2 (en) * | 1989-12-04 | 1993-10-14 | Deutsche Aerospace Airbus | satellite |
| DE102022114410A1 (en) | 2022-06-08 | 2023-12-14 | Mt Aerospace Ag | Central tube for satellites and spacecraft |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3700193A (en) * | 1971-01-14 | 1972-10-24 | Nasa | A method of delivering a vehicle to earth orbit and returning the reusable portion thereof to earth |
| FR2472509A1 (en) * | 1979-12-27 | 1981-07-03 | Organisation Europ Rech Sp | ARTIFICIAL SATELLITE CONFIGURATION FOR CONTINUOUS ATTITUDE MONITORING FOLLOWING THREE AXES |
| FR2476018A1 (en) * | 1980-02-14 | 1981-08-21 | Org Europeene De Rech | CONFIGURATION OF SATELLITES FOR GEOSTATIONARY MISSION |
-
1981
- 1981-01-17 DE DE19813101368 patent/DE3101368A1/en not_active Ceased
- 1981-10-20 FR FR8119703A patent/FR2498156A1/en active Pending
- 1981-11-18 IT IT25159/81A patent/IT1139789B/en active
- 1981-12-02 JP JP56192999A patent/JPS57122000A/en active Pending
-
1982
- 1982-01-14 GB GB8201033A patent/GB2091194A/en not_active Withdrawn
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0134288A1 (en) * | 1983-09-03 | 1985-03-20 | ERNO Raumfahrttechnik Gesellschaft mit beschränkter Haftung | Satellite system with variable configuration |
| US4834325A (en) * | 1985-03-20 | 1989-05-30 | Space Industries, Inc. | Modular spacecraft system |
| FR2593466A1 (en) * | 1985-10-30 | 1987-07-31 | Rca Corp | SPACE VEHICLE STRUCTURE FOR ASSEMBLY AND TROUBLESHOOTING IN ORBIT |
| US4880187A (en) * | 1986-01-16 | 1989-11-14 | Trw Inc. | Multipurpose modular spacecraft |
| US4865514A (en) * | 1986-10-03 | 1989-09-12 | Hitachi, Ltd. | Manipulator system with small arm removably attachable at points along large arm |
| FR2636040A1 (en) * | 1988-09-06 | 1990-03-09 | Matra | Space vehicle for a mission in microgravity and method of experimentation using such a vehicle |
| EP0541052A1 (en) * | 1991-11-05 | 1993-05-12 | Hitachi, Ltd. | Spacecraft system |
| US5372340A (en) * | 1991-11-05 | 1994-12-13 | Hitachi, Ltd. | Spacecraft system |
| US5429328A (en) * | 1992-11-16 | 1995-07-04 | Environmental Research Institute Of Michigan | Spacecraft payload exchange system |
| EP0826596A1 (en) * | 1996-08-29 | 1998-03-04 | Space Systems/Loral, Inc. | Space platform assembly for attachment to a space station |
| US5950965A (en) * | 1997-07-17 | 1999-09-14 | Lockheed Martin Corporation | Split shell spacecraft |
| US6149104A (en) * | 1998-04-01 | 2000-11-21 | Trw Inc. | Structural layout for spacecraft including specialized compartment configuration |
| US6193193B1 (en) * | 1998-04-01 | 2001-02-27 | Trw Inc. | Evolvable propulsion module |
| CN105035360A (en) * | 2015-07-31 | 2015-11-11 | 上海卫星工程研究所 | Cabin-segmentation type separable platform configuration based on four-point connection |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2498156A1 (en) | 1982-07-23 |
| IT1139789B (en) | 1986-09-24 |
| JPS57122000A (en) | 1982-07-29 |
| DE3101368A1 (en) | 1982-07-29 |
| IT8125159A0 (en) | 1981-11-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| GB2091194A (en) | Apparatus for carrying out experiments under conditions of weightlessness | |
| EP0541052B1 (en) | Spacecraft system | |
| US20230382566A1 (en) | Spacecraft systems airlock for international space station access and interface and methods of operation | |
| Palii | State of the art in the development of orbital industrial platforms | |
| RU2181094C1 (en) | Multi-functional attended spacecraft and method of conducting multi-purpose scientific applied researches by means of this spacecraft | |
| Rosmalen | The International Space Station past, Present and Future–an Overview | |
| Mory et al. | EUROPEAN RETRIEVABLE CARRIER (EURECA) AN EVOLUTIONARY SPACE CARRIER FOR MICROGRAVITY, EARTH OBSERVATION AND TECHNOLOGY DEMONSTRATION | |
| Mory | EURECA Programme Manager Space Transportation Systems/LTPO European Space Agency, Paris and G. Seibert | |
| Caime et al. | Paper Session IC-Autonomous Microgravity Industrial Carrier (AMICA) Initiative | |
| Arnold | NASA's commercial research plans and opportunities | |
| WITHEE | Research and applications modules/RAM/-A family of payload carriers | |
| Abbott | Solar thermal materials processing platform | |
| Freitag | Space Station Planning 1984 | |
| Herman et al. | Technical Aspects of the United States Space Station | |
| Huber | Orbital maneuvering vehicle: A new capability | |
| Ollendorf | Telerobotic electronic materials processing experiment | |
| Bartoe | Research plans for the International Space Station—Research begins this year! | |
| Aepli et al. | Space Station Payload Accommodation | |
| Kasturirangan et al. | ISRO spacecraft technology evolution | |
| Volz et al. | The General-purpose Reusable Attached Station Platform (GRASP) | |
| Kutzer | The European Columbus Programme | |
| Messerschmid et al. | The International Space Station | |
| Schmidt | Automation and Robotics for Experiment Operations in an Enhanced Man Tended Free Flyer (EMTFF) | |
| Moe | An early in-space platform for technology development & demonstration of robotic assembly and servicing | |
| Interian | Teleoperator systems for manned space missions |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |