DE102022130071A1 - Propulsion unit based on the recoil principle for a payload in space - Google Patents

Abstract

The invention relates to a propulsion unit (2) based on the recoil principle with a support structure (10), at least one controllable engine (4) which is attached to the support structure (10), a fuel supply for the engine (4), a thrust control, a mechanical payload interface (30) for permanently coupling a payload (1) to the propulsion unit (2), a mechanical launch interface (32) for coupling the propulsion unit (2) with the payload (1) attached to it to a carrier rocket, and a data interface to the payload (1) and to the carrier rocket.

Description

The invention relates to a propulsion unit based on the recoil principle for a payload, for example a satellite, which is placed into orbit by means of a carrier rocket.

If we ignore air friction and solar wind, such a payload (hereinafter also referred to as a "spacecraft") is only affected by the gravitational forces of neighboring masses in the Newtonian sense. If a spacecraft wants to leave the trajectory determined by these gravitational forces, it requires a propulsion system that exerts an additional force on the spacecraft and thus changes its momentum. With regard to mobility, i.e. the possibility of leaving the trajectory determined by the mass forces, several types of propulsion systems can be distinguished.

On the one hand, there are propulsion systems (hereinafter referred to as "integrated propulsion systems") which are installed directly in the spacecraft. A spacecraft with an integrated propulsion system benefits from permanent mobility (assuming permanent functionality of the propulsion system) and the associated ability to make changes to its orbit and orientation. This is particularly relevant with regard to reaching the desired orbit after separation from the launch vehicle ("last mile transfer"), maintaining position and orientation during the operational lifetime of the spacecraft ("attitude and orbit control" AOCS), carrying out rendezvous or docking maneuvers with other spacecraft in the context of maintenance, repair and refueling work, carrying out evasive maneuvers to avoid collisions with other objects and the controlled departure from orbit at the end of the satellite's lifetime ("de-orbiting"). In addition, a spacecraft with an integrated propulsion system benefits from efficient mass and volume distribution, because the spacecraft's installation space is used as efficiently as possible and system redundancy only occurs where it is explicitly desired.

On the other hand, external propulsion systems are known that are relied upon by spacecraft that are not equipped with an integrated propulsion system. Such external propulsion systems can themselves be considered as specialized spacecraft that move the actual spacecraft in space for a limited period of the spacecraft's mission. In this case, the spacecraft to be moved merely represents the payload of the external propulsion system and has little or no influence on its behavior. Examples of this are launch vehicles and their respective stages, space tugs, kickstages, orbital transfer vehicles (OTVs) and landing vehicles that transport payloads. The advantages of external propulsion systems are primarily that the independence of the spacecraft and the propulsion system is maximized. The entire complexity of the propulsion technology is shifted to a separate system, with corresponding advantages in terms of improved interchangeability and modularity, reduced systemic interdependence and simplified integration.

• Ansatz 1 „Gimbal“:
  • Es wird mindestens ein Triebwerk verwendet, welches beweglich montiert ist und somit translativ und/oder rotatorisch ausgerichtet werden kann.
• Ansatz 2 „Differentieller Schub“:
  • Es werden mindestens drei Triebwerke verwendet. Diese sind zwar unbeweglich montiert, können jedoch unabhängig voneinander ihren Schub ändern und somit den Schubvektor, der vom gesamten Antriebssystem erzeugt wird, beeinflussen.
• Ansatz 3: „Steuerungstriebwerke“:
  • Es werden mehrere Triebwerke verwendet, welche unbeweglich montiert und in unterschiedliche Richtungen ausgerichtet sind. Sie können ihren Schub nicht ändern, sind jedoch in der Lage unabhängig voneinander ein- und ausschalten und somit den Gesamtschubvektor zu beeinflussen.

The continuous change of the thrust vector of a spacecraft's propulsion system can basically be accomplished in three ways:

• Approach 1 “Gimbal”:
  • At least one engine is used, which is movably mounted and can therefore be aligned translationally and/or rotationally.
• Approach 2 “Differential thrust”:
  • At least three engines are used. Although they are mounted immobile, they can change their thrust independently of each other and thus influence the thrust vector generated by the entire propulsion system.
• Approach 3: “Control engines”:
  • Several engines are used, which are mounted immobile and pointing in different directions. They cannot change their thrust, but are able to switch on and off independently of each other and thus influence the overall thrust vector.

While approach 2 is very commonly used in aircraft with independently controllable engines (e.g. multicopters with electric motors) due to its mechanical simplicity, it is less widely used in spacecraft than approaches 1 and 3. This is because most engines used by spacecraft do not have the ability to control thrust. Exceptions to this are landing vehicles (e.g. Sky Crane, which is used by NASA to land vehicles on Mars).

The object of the invention is to provide a propulsion system for a spacecraft that combines the respective advantages of integrated and external propulsion systems.

To achieve this object, according to the invention, a drive unit is provided with a support structure, at least one controllable engine that is attached to the support structure, a fuel supply for the engine, a thrust control, a mechanical payload interface for permanently coupling a payload to the drive unit, a mechanical launch interface for coupling the drive unit with the payload attached to it to a carrier rocket, and a data interface and an electronic interface to the payload and the carrier rocket. The drive unit according to the invention represents a novel system that is conceptually positioned between an integrated and an external drive system. The drive unit according to the invention extends the mobility of a spacecraft that has an integrated drive system that is inadequate for the specific application. The drive unit according to the invention has at least one complete and thrust-controllable drive train and is connected to the spacecraft via a mechanical and electronic interface and a data interface before launch into space. Since the thrust vector of the propulsion unit according to the invention can be influenced by means of differential thrust control, it is less sensitive to the mass distribution of the connected spacecraft or can compensate for it and is thus compatible with a large number of different satellites.

Preferably, the payload interface and the launch interface are of the same type. This makes it possible to arrange the propulsion unit between the launch vehicle and the payload without having to change the interface on the payload that was previously used to connect it to the launch vehicle. In the same way, the interface on the launch vehicle that was previously used to connect the payload can continue to be used unchanged.

The fuel supply preferably consists of a fuel and an oxidizer so that a high energy density is ensured.

The engine is preferably rigidly attached to the support structure. This reduces the weight, technical complexity and cost of the drive unit, since no mechanisms and actuators are required to pivot the engine.

Preferably, several engines are provided, in particular four engines. In this way, by suitably controlling the engines, which are preferably continuously controllable with regard to the thrust generated, the thrust control can change the total thrust vector in terms of magnitude, orientation and line of action by means of continuous thrust control.

According to one embodiment, it is characterized in that at least two engines are positioned slightly obliquely to one another. This allows the payload to be completely stabilized about all three axes of rotation, even if all engines are rigidly attached to the drive unit. This results in low costs and low complexity.

According to one embodiment, an interface for refueling is provided so that the service life of the drive unit and the associated payload can be extended.

Subsystems for thermal management, energy management, an inertial measurement unit and/or flight control are preferably integrated into the propulsion unit so that the propulsion unit is fully functional in these respects without being dependent on corresponding subsystems of the payload.

The drive unit itself preferably does not have its own communication system, but accesses the communication system of the payload coupled to it. This reduces the costs for the drive unit; it is sufficient if the data interface of the drive unit is designed to exchange communication data between the drive unit and the payload, which the payload receives via a communication unit.

• 1 in einer perspektivischen Ansicht eine erfindungsgemäße Antriebseinheit gekoppelt mit einer Nutzlast,
• 2 eine perspektivische Explosionsansicht der Baugruppe aus Antriebseinheit und Nutzlast von 2,
• 3 in einer perspektivischen Draufsicht die erfindungsgemäße Antriebseinheit der Baugruppe von 1,
• 4 in einer perspektivischen Unteransicht die erfindungsgemäße Antriebseinheit der Baugruppe von 1,
• 5 in einer perspektivischen Seitenansicht die erfindungsgemäße Antriebseinheit der Baugruppe von 1, wobei die in der Antriebseinheit vorgesehenen Tanks und weiteren Baugruppen wie Flugsteuerung und Batterien nicht dargestellt sind, und
• 6 eine Draufsicht auf die Antriebseinheit der Baugruppe von 1.

The invention is described below using an embodiment shown in the accompanying drawings, in which:

• 1 in a perspective view a drive unit according to the invention coupled with a payload,
• 2 an exploded perspective view of the drive unit and payload assembly of 2 ,
• 3 in a perspective top view the drive unit according to the invention of the assembly of 1 ,
• 4 in a perspective bottom view the drive unit according to the invention of the assembly of 1 ,
• 5 in a perspective side view the drive unit according to the invention of the assembly of 1 , whereby the tanks and other components provided in the drive unit such as flight control and batteries are not shown, and
• 6 a top view of the drive unit of the assembly of 1 .

In the 1 to 6 A payload 1 is shown schematically, to which a drive unit 2 is assigned.

Payload 1 may in particular be a satellite.

Generally speaking, the drive unit 2 serves to change the momentum of the payload 1. In the example of the satellite, the drive unit 2 serves in particular to move the satellite to a different orbit or to accelerate it to a different orbital speed.

The propulsion unit comprises a complete and thrust-controllable drive train based on the recoil principle and comprising several engines 4 .

Each engine 4 has an injector 6 and a thrust nozzle 8.

The engines 4 are rigidly attached to a support structure 10 of the drive unit 2.

In the embodiment shown, each engine 4 is attached to a flame arrester 11, which in turn is attached to the support structure 10. The flame arrester 11 is arranged in particular between the thrust nozzles 8 and the support structure 10.

In the embodiment shown, the support structure has a generally square shape in a plan view and a rectangular shape in the side views, wherein the height of the rectangle is smaller than the side length of the square.

The dimensions of the square essentially correspond to the dimensions of the cross-section of the payload 1, so that the drive unit 2 does not or only insignificantly protrudes beyond the base area of the payload 1.

However, other basic shapes of the drive unit 2 are also possible, for example octagonal, where four of the side surfaces of the octagon are aligned parallel to the side surfaces of the payload 1 and four side surfaces are used to attach the engines 4.

Depending on the required volume within the drive unit 2, it can also protrude beyond the payload.

A fuel supply is provided for the engines. This has an oxidizer tank 12 for each engine 4 and a common fuel tank 14 (see in particular 6 ). The piping used to supply the oxidizer and fuel to the engines 4 is provided with the reference number 16. A tank nozzle 18 can also be seen as part of the fuel supply. The control system for the engines 4 is not shown here for the sake of clarity.

Furthermore, a safety valve 24 is provided for the fuel supply.

The propulsion unit also has the usual subsystems necessary for functionality, such as a flight control system 20 with electronics and inertial measurement unit (IMU), thermal management and batteries 22.

If the engines 4 are aligned parallel to each other, the payload 1 can only be stabilized about two axes (pitch and yaw) with differential thrust from them. If a rolling motion is desired, either at least two additional engines would have to be provided, using a thrust vector transverse to the direction of the thrust vector of the engines 4 aligned parallel to each other, or instead of rigidly connecting the engines, at least one of them would have to be mounted so that it can pivot. Both variants are associated with a high level of effort (both in terms of control and construction effort and the resulting weight).

Alternatively, in order to enable roll control, at least two engines 4 can be set at slightly opposite angles (i.e. arranged so that their thrust vector is aligned obliquely to the longitudinal axis of the spacecraft formed by the propulsion unit 2 and the payload 1). This results in thrust vectors that have a component that leads to a roll movement.

The slightly inclined positioning of at least two engines 4 results in a slight reduction in thrust in the forward direction and thus a reduction in the overall efficiency of the propulsion system. However, this loss is negligible compared to the effort that would be required for alternative variants that enable roll control.

On the base side of the drive unit, which faces the injectors 6 of the engines 4, the drive unit 2 has a payload interface 30. This serves for fixed coupling with the payload 1. “Fixed” here means that the connection between the payload 1 and the drive unit 2 is not to be changed again during the service life of the payload 1. is released. The drive unit 2 is permanently assigned to a specific payload 1.

The drive unit 2 has a launch interface 32 on its side facing away from the payload interface, i.e. an interface with which the drive unit 2 can be connected to a launch vehicle. The coupling with the launch vehicle can be released as soon as the drive unit 2 with the payload 1 is in the desired orbit.

The launch interface 32 is geometrically identical to the launch interface that the payload 1 has. This makes it possible to "interpose" the propulsion unit 2 between the payload 1 and the launch vehicle without any significant modifications to the launch vehicle being necessary.

Another key feature of the drive unit 2 is that it does not have its own communication system, i.e. no antenna, no transmitter and no receiver with which communication with a control station on earth takes place. Instead, the drive unit 2 has a data interface (not visible in the figures) via which the data required to control the drive unit 2 is transmitted from the payload 1.

• Im Gegensatz zu einem integrierten Antriebssystem, welches typischerweise an einigen unterschiedlichen Stellen mit der Nutzlast verbunden ist, ist die Antriebseinheit 2 nur über genau eine mechanische und genau eine elektronische Schnittstelle mit der Nutzlast verbunden. Außerdem ist genau eine Datenschnittstelle zur Nutzlast hin vorgesehen.
• Im Gegensatz zu einem integrierten Antriebssystem, welches zumindest teilweise im Bauraum der Nutzlast untergebracht ist, wird die Antriebseinheit 2 vollständig außen an der Nutzlast befestigt.
• Im Gegensatz zu einem integrierten Antriebssystem, welches keine Schnittstelle zur Trägerrakete hat, dient die Antriebseinheit 2 direkt als die Schnittstelle zur Trägerrakete.
• Im Gegensatz zu einem integrierten Antriebssystem, welches nicht über eine Flugsteuerung, eine IMU, Thermalmanagement und Batterien verfügt, sondern auf jene der Nutzlast zugreift, verfügt die Antriebseinheit 2 direkt über diese.

The drive unit 2 differs from an integrated drive system with regard to the following features:

• In contrast to an integrated drive system, which is typically connected to the payload at several different points, the drive unit 2 is only connected to the payload via exactly one mechanical and exactly one electronic interface. In addition, exactly one data interface to the payload is provided.
• In contrast to an integrated drive system, which is at least partially housed in the installation space of the payload, the drive unit 2 is completely attached to the outside of the payload.
• In contrast to an integrated propulsion system, which has no interface to the launch vehicle, the propulsion unit 2 serves directly as the interface to the launch vehicle.
• In contrast to an integrated propulsion system, which does not have a flight controller, an IMU, thermal management and batteries, but accesses those of the payload, the propulsion unit 2 has these directly.

• Im Gegensatz zu einem integrierten Antriebssystem, welches im Allgemeinen als unzusammengebaute Baugruppe an den Kunden überstellt wird, kann die Antriebseinheit 2 als voll integriertes Produkt an den Kunden übergeben werden. Dies kann auch bedeuten, dass die Tanks der Antriebseinheit 2 bereits mit Treibstoff und Oxidator befüllt sind.
• Im Gegensatz zu einem integrierten Antriebssystem ist der Integrationsaufwand der Antriebseinheit 2 deutlich reduziert. Dies ist mit Kosten- und Zeitersparnis verbunden.
• Im Gegensatz zu einem integrierten Antriebssystem, welches nur unter Inkaufnahme großer Nachteile (z.B. Ineffizienz in Hinblick auf Volumen und Massenverteilung) als Plug-and-Play System ausgeführt werden kann, ist die Antriebseinheit 2 grundsätzlich als Plug-and-Play Produkt ausgelegt.
• Im Gegensatz zu einem integrierten Antriebssystem ist der Aufwand, welcher mit Wartungs- und Reparaturarbeiten an der Antriebslösung verbunden ist, deutlich reduziert. Die Antriebseinheit 2 ist für solche Tätigkeiten räumlich deutlich besser erreichbar. Im Extremfall kann sogar die komplette Antriebseinheit deutlich schneller ausgetauscht werden als ein vergleichbares integriertes Antriebssystem.
• Im Gegensatz zu einem integrierten Antriebssystem, welches direkt ein Teil der Nutzlast ist, stellt die Antriebseinheit 2 lediglich ein Modul zur Erweiterung der Fähigkeiten der Nutzlast dar.
• Im Gegensatz zu einem integrierten Antriebssystem ist die Nutzlast auch ohne die Antriebseinheit 2 voll funktionsfähig, sie ist lediglich weniger mobil.
• Im Gegensatz zu einem integrierten Antriebssystem muss beim Design der Nutzlast die Antriebseinheit 2 kaum berücksichtigt werden. Selbst wenn es beim Design der Nutzlast nicht vorgesehen wurde, kann es nachträglich - nach minimalen Anpassungen an die Nutzlast - zu den meisten Satelliten hinzugefügt werden.
• Im Gegensatz zur Verwendung eines integrierten Antriebssystems, welche bereits früh in der Designphase eine Definition von Antriebstechnologie, Masse, Volumen und Bauform der Antriebslösung erfordert, ermöglicht die Verwendung die Antriebseinheit 2 auch kurzfristige Änderungen an der Antriebslösung (z.B. Schub, Treibstoffmasse, Gesamtimpuls) und somit dem Missionsprofil.
• Im Gegensatz zur Verwendung eines integrierten Antriebssystems, welches für Funktionstüchtigkeit auf in der Nutzlast vorhandene, geeignete Flugsteuerung, eine IMU, Thermalmanagement und Batterien angewiesen ist, hat die Antriebseinheit 2 diese bereits intern verbaut.
• Im Gegensatz zur Verwendung eines integrierten Antriebssystems ermöglicht die Antriebseinheit 2 die Ausstattung derselben Nutzlast in Kombination mit sehr unterschiedlichen Antriebslösungen und somit entsprechend erweiterte Flexibilität.
• Im Gegensatz zu einem integrierten Antriebssystem, welches signifikante Anforderungen an die Nutzlast stellt (z.B. in Hinblick auf thermale Umgebung), müssen beim Design der Nutzlast keine entsprechenden Anforderungen berücksichtigt werden.
• Im Gegensatz zur Verwendung eines integrierten Antriebssystems ersetzt die Antriebseinheit 2 die Schnittstelle zur Trägerrakete. Dies spart kundenseitig Kosten und reduziert die Komplexität der Nutzlast.

This gives the drive unit 2 the following advantages over an integrated drive system:

• In contrast to an integrated drive system, which is generally delivered to the customer as an unassembled unit, the drive unit 2 can be delivered to the customer as a fully integrated product. This can also mean that the tanks of the drive unit 2 are already filled with fuel and oxidizer.
• In contrast to an integrated drive system, the integration effort of drive unit 2 is significantly reduced. This is associated with cost and time savings.
• In contrast to an integrated drive system, which can only be implemented as a plug-and-play system at the expense of major disadvantages (e.g. inefficiency in terms of volume and mass distribution), the drive unit 2 is fundamentally designed as a plug-and-play product.
• In contrast to an integrated drive system, the effort involved in maintenance and repair work on the drive solution is significantly reduced. Drive unit 2 is much easier to reach for such activities. In extreme cases, the entire drive unit can even be replaced much more quickly than a comparable integrated drive system.
• In contrast to an integrated propulsion system, which is directly part of the payload, the propulsion unit 2 is merely a module to extend the capabilities of the payload.
• In contrast to an integrated drive system, the payload is fully functional even without the drive unit 2, it is just less mobile.
• Unlike an integrated propulsion system, the propulsion unit 2 hardly needs to be taken into account when designing the payload. Even if it was not included in the payload design, it can be added later to most satellites - after minimal adjustments to the payload.
• In contrast to the use of an integrated propulsion system, which requires a definition of the propulsion technology, mass, volume and design of the propulsion solution early in the design phase, the use of the propulsion unit 2 also enables short-term changes to the propulsion solution (e.g. thrust, fuel mass, total impulse) and thus the mission profile.
• In contrast to the use of an integrated propulsion system, which depends on suitable flight control, an IMU, thermal management and batteries present in the payload for functionality, the propulsion unit 2 already has these installed internally.
• In contrast to the use of an integrated drive system, Drive Unit 2 enables the same payload to be equipped in combination with very different drive solutions and thus offers correspondingly increased flexibility.
• In contrast to an integrated propulsion system, which places significant demands on the payload (e.g. with regard to thermal environment), no corresponding requirements need to be taken into account when designing the payload.
• In contrast to the use of an integrated propulsion system, propulsion unit 2 replaces the interface to the launch vehicle. This saves costs for the customer and reduces the complexity of the payload.

• Im Gegensatz zu einem externen Antriebssystem, welches in der Lage ist, selbstständig im Weltall zu operieren, ist die Antriebseinheit 2 immer auf eine Nutzlast angewiesen, an welcher sie angebracht ist, um funktionstüchtig zu sein. Es ist somit vielmehr ein Subsystem als ein eigenständiges Raumfahrzeug.
• Im Gegensatz zu einem externen Antriebssystem, welches über ein Kommunikationssystem verfügt, verfügt die Antriebseinheit 2 nicht über dieses, sondern muss auf das der Nutzlast zugreifen.
• Im Gegensatz zu einem externen Antriebssystem, welches die Fähigkeit hat, mehr als eine Nutzlast zu transportieren - entweder seriell oder parallel - , ist jede einzelne Antriebseinheit 2 für lediglich eine einzelne Nutzlast gedacht.
• Im Gegensatz zu einem externen Antriebssystem, welches über einen Trennmechanismus und/oder Verbindungsmechanismus zur Nutzlast verfügt, ist die Antriebseinheit 2 dauerhaft an der Nutzlast angebracht und verfügt über keine Fähigkeit der selbstständigen Trennung und/oder Verbindung von der Nutzlast bzw. mit der Nutzlast.

The drive unit 2 differs from an external drive system with regard to the following features:

• In contrast to an external propulsion system, which is able to operate independently in space, the propulsion unit 2 is always dependent on a payload to which it is attached in order to function. It is therefore more of a subsystem than an independent spacecraft.
• In contrast to an external drive system, which has a communication system, the drive unit 2 does not have this, but must access that of the payload.
• In contrast to an external propulsion system, which has the ability to transport more than one payload - either serially or in parallel - each individual propulsion unit 2 is intended for only a single payload.
• In contrast to an external drive system, which has a separation mechanism and/or connection mechanism to the payload, the drive unit 2 is permanently attached to the payload and has no ability to independently separate and/or connect from or to the payload.

• Im Gegensatz zu einem externen Antriebssystem, welches nur in Ausnahmesituationen dauerhaft mit der Nutzlast verbunden bleibt, ist die Antriebseinheit 2 permanent mit dieser verbunden. Dies ermöglicht Mobilität über die gesamte Lebensdauer der Nutzlast hinweg. Als nicht abschließende Aufzählung umfasst dies Orbit Transfers sowie Anpassungen der Position und der Ausrichtung der Nutzlast zum Zwecke
  • - des Erreichens des erwünschten Orbits nach dem Trennen von der Trägerrakete,
  • - der Veränderung der Mission,
  • - der Durchführung von Annäherungs- und Rendezvous-Manövern mit anderen Raumfahrzeugen oder Nutzlasten, beispielsweise zum Zwecke der Wartung, Reparatur oder Wiederbetankung,
  • - des Ausweichens von Objekten im Weltall,
  • - der Kompensation von atmosphärischem Strömungswiderstand, und/oder
  • - der Entsorgung der Nutzlast.
• Im Gegensatz zu einem externen Antriebssystem, welches das Telekommunikationsmodul redundant mit der Nutzlast bzw. dem Raumfahrzeug ausgeführt hat, um selbstständig im Weltall tätig sein zu können, ist dieses bei der Antriebseinheit 2 nicht mit der Nutzlast redundant.
• Im Gegensatz zu einem externen Antriebssystem, welches über mindestens zwei Trennmechanismen (einem zur Trägerrakete sowie mindestens einem zur Nutzlast/zu den Nutzlasten) verfügt, besitzt die Antriebseinheit 2 nur einen Trennmechanismus zur Trägerrakete. Dies spart Masse und Komplexität.

This gives the drive unit 2 the following advantages over an external drive system:

• In contrast to an external propulsion system, which only remains permanently connected to the payload in exceptional situations, the propulsion unit 2 is permanently connected to it. This enables mobility over the entire service life of the payload. As a non-exhaustive list, this includes orbit transfers as well as adjustments to the position and orientation of the payload for the purpose of
  • - reaching the desired orbit after separation from the launch vehicle,
  • - the change of mission,
  • - carrying out approach and rendezvous manoeuvres with other spacecraft or payloads, for example for the purposes of maintenance, repair or refuelling,
  • - avoiding objects in space,
  • - compensation of atmospheric flow resistance, and/or
  • - disposal of the payload.
• In contrast to an external propulsion system, which has implemented the telecommunications module redundantly with the payload or the spacecraft in order to be able to operate independently in space, the propulsion unit 2 is not redundant with the payload.
• In contrast to an external propulsion system, which has at least two separation mechanisms (one to the launch vehicle and at least one to the payload(s), the propulsion unit 2 has only one separation mechanism to the launch vehicle. This saves mass and complexity.

Claims (12)

Propulsion unit (2) based on the recoil principle with a support structure (10), at least one controllable engine (4) which is attached to the support structure (10), a fuel supply for the engine (4), a thrust control, a mechanical payload interface (30) for permanently coupling a payload (1) to the propulsion unit (2), a mechanical launch interface (32) for coupling the propulsion unit (2) with the payload (1) attached thereto to a carrier rocket, and a data interface and an electronic interface to the payload (1) and to the carrier rocket. Drive unit according to Claim 1 , characterized in that the payload interface (30) and the launch interface (32) are of the same type. Drive unit according to Claim 1 or Claim 2 , characterized in that the fuel supply consists of a fuel and an oxidizer. Drive unit according to one of the preceding claims, characterized in that the engine (4) is rigidly attached to the support structure (10). Drive unit according to one of the preceding claims, characterized in that several engines (4) are provided, in particular four engines (4). Drive unit according to Claim 5 , characterized in that at least two engines are positioned slightly obliquely to each other. Drive unit according to one of the preceding claims, characterized in that the thrust control is designed to change the total thrust vector by means of continuous thrust control in terms of magnitude, orientation and line of action. Drive unit according to one of the preceding claims, characterized in that an interface (18) for refueling is provided. Drive unit according to one of the preceding claims, characterized in that a thermal management subsystem is integrated. Drive unit according to one of the preceding claims, characterized in that an energy management subsystem is integrated. Drive unit according to one of the preceding claims, characterized in that an inertial measuring unit and/or a flight control are integrated. Drive unit according to one of the preceding claims, characterized in that the data interface is designed for the exchange of communication data between the drive unit and the payload, which the payload (1) receives via a communication unit.

Images