DE19545711C1 - Reusable carrier body as starting aid for flight craft - Google Patents

Reusable carrier body as starting aid for flight craft

Info

Publication number
DE19545711C1
DE19545711C1 DE19545711A DE19545711A DE19545711C1 DE 19545711 C1 DE19545711 C1 DE 19545711C1 DE 19545711 A DE19545711 A DE 19545711A DE 19545711 A DE19545711 A DE 19545711A DE 19545711 C1 DE19545711 C1 DE 19545711C1
Authority
DE
Germany
Prior art keywords
support body
carrier body
engine
flight
aircraft
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.)
Expired - Fee Related
Application number
DE19545711A
Other languages
German (de)
Inventor
Holger Dipl Ing Stockfleth
Johann Dipl Ing Spies
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus DS GmbH
Original Assignee
Daimler Benz Aerospace AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Daimler Benz Aerospace AG filed Critical Daimler Benz Aerospace AG
Priority to DE19545711A priority Critical patent/DE19545711C1/en
Priority to EP96118411A priority patent/EP0778200A3/en
Priority to RU96122836A priority patent/RU2120398C1/en
Priority to JP8326982A priority patent/JPH09175499A/en
Application granted granted Critical
Publication of DE19545711C1 publication Critical patent/DE19545711C1/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D5/00—Aircraft transported by aircraft, e.g. for release or reberthing during flight
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/002—Launch systems
    • B64G1/005—Air launch
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/14—Space shuttles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/74—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant
    • F02K9/76—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants
    • F02K9/766—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants with liquid propellant

Landscapes

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

Abstract

The carrier body (1) has a land carriage (4) and a propellant fuel tank for connection with the engine of the flight craft. The engine forms the drive for the entire assembly and during the transport phase is supplied solely from the fuel tank of the carrier body. The flight craft is arranged under the support body in the area of the land carriage. The fuel tank has a larger capacity so that the achievable end speed of the flight craft can be increased.

Description

Die Erfindung bezieht sich auf einen wiederverwendbaren Tragkörper mit aerodynamischen Auftriebsmitteln, zur Starthilfe eines mit eigenem Triebwerk und Treibstoff­ tanks ausgerüsteten Fluggerätes.The invention relates to a reusable Support body with aerodynamic buoyancy means, for Jump start one with its own engine and fuel tanks equipped aircraft.

Bei Ausbildungen dieser Art besteht das Problem in der konsequenten Nutzung des oder der Antriebe, damit einerseits die Nutzlastkapazität erhöht und anderer­ seits ein hohes Einsparpotential erzielbar ist.The problem with training of this type is that consequent use of the drive or drives, so on the one hand increases the payload capacity and on the other a high savings potential can be achieved.

Aus der DE 37 40 645 A1 ist ein gattungsgemäßer Trag­ körper bekannt. Hierbei besteht der Mangel, daß es erforderlich ist, den wiederverwendbaren Tragkörper als sogenannte erste Stufe triebwerkmäßig voll funktionsfähig auszurüsten und eine Umschaltung für die Stufentrennung vorzunehmen.DE 37 40 645 A1 is a generic support body known. Here there is a lack that it is necessary to use the reusable support body as the so-called first stage engine-full functional equipment and a switchover for the Stage separation.

Die Aufgabe der Erfindung besteht darin, eine gattungs­ gemäße Anordnung zu verbessern und eine Nutzung des Antriebes des abzusetzenden Fluggerätes für die Gesamt­ anordnung zu ermöglichen sowie eine optimierte Treib­ stofflagerung zu gewährleisten.The object of the invention is a genus order to improve and use the Drive of the aircraft to be sold for the total to enable arrangement and an optimized propellant to ensure fabric storage.

Die Lösung dieser Aufgabe erfolgt erfindungsgemäß da­ durch, daß der Tragkörper ein Landefahrwerk und Treib­ stofftanks zur Verbindung mit dem Triebwerk des Flug­ gerätes aufweist, wobei dessen Triebwerk als Antrieb für die Gesamtanordnung ausgebildet ist und während der Transportphase ausschließlich aus den Treibstofftanks des Tragkörpers versorgt wird.This object is achieved according to the invention through that the support body a landing gear and propulsion fabric tanks for connection to the flight engine Has device, the engine as a drive is designed for the overall arrangement and during the Transport phase exclusively from the fuel tanks the support body is supplied.

Die erzielten Vorteile bestehen darin, daß die Nutz­ lastkapazität einer nicht wiederverwendbaren Rakete in etwa verdoppelbar ist oder eine nicht wiederverwendbare Stufe eines mehrstufigen Trägers bzw. dessen Booster durch den wiederverwendbaren Tragkörper ersetzt werden kann. Ferner ist eine Einsparung von Starthilfen, wie ein Starttisch bei Senkrechtstartern oder Beschleuni­ gungsschlitten bei Horizontalstartern möglich und es braucht die Flügelgröße eines Horizontalstarters nur für die Landung dimensioniert werden. Die Flügelbe­ lastung wird somit beim Anheben des Bahnwinkels beim Horizontalstart geringer, weil dieses Manöver haupt­ sächlich den Tragkörper belastet. Im anderen Fall ist dieser Lastfall bestimmend und führt somit zu hohen Flügelstrukturmassen.The advantages achieved are that the utility load capacity of a non - reusable missile in is about doubled or not reusable Level of a multi-level carrier or its booster be replaced by the reusable support body can. Furthermore, a saving of starting aids, such as a starting table for vertical starters or accelerators slide with horizontal starters possible and it only needs the wing size of a horizontal starter be dimensioned for landing. The Flügelbe load is thus when lifting the path angle at Horizontal start less because of this maneuver at all the load on the supporting body. In the other case it is this load case determines and thus leads to high Wing structure masses.

Ein Ausführungsbeispiel der Erfindung ist in der Zeichnung schematisch dargestellt. Es zeigen:An embodiment of the invention is in the Drawing shown schematically. Show it:

Fig. 1 eine Seitenansicht eines Tragkörpers mit unterhalb aufgehängtem und absetzbaren Flug­ gerät, Fig. 1 is a side view of device with a supporting body underneath a suspended and settleable flight,

Fig. 2 eine Vorderansicht des Tragkörpers gemäß Fig. 1 und Fig. 2 is a front view of the support body according to FIGS. 1 and

Fig. 3 eine Draufsicht auf den Tragkörper. Fig. 3 is a plan view of the support body.

Bei der gezeigten Anordnung ist mit einem Tragkörper 1 als Starthilfefluggerät ein Fluggerät 2, wie beispiels­ weise eine Rakete verbunden. Dieses Fluggerät 2 ist mit einem Primärantrieb für die Gesamtanordnung versehen, so daß der Tragkörper 1 keinen Antrieb benötigt.In the arrangement shown, an aircraft 2 , such as, for example, a rocket, is connected to a support body 1 as a jump-starting aircraft. This aircraft 2 is provided with a primary drive for the overall arrangement, so that the support body 1 does not require a drive.

Das Fluggerät 2 ist unterhalb oder oberhalb des Rumpfes des Tragkörpers 1 zwischen einem zugeordneten Fahrwerk 4 angeordnet und während des Fluges abkoppelbar ausge­ führt.The aircraft 2 is arranged below or above the fuselage of the support body 1 between an associated landing gear 4 and leads out uncoupled during the flight.

Im Rumpf des Tragkörpers 1 sind Treibstofftanks ange­ ordnet, die über Verbindungen 3 mit dem Antrieb des Fluggerätes 2 zur Treibstoffversorgung als Primäran­ trieb verbunden sind. In den Verbindungen sind entsprechende Trennventile vorgesehen, damit ein problemloses Entkoppeln möglich ist.In the fuselage of the support body 1 , fuel tanks are arranged, which are connected via connections 3 with the drive of the aircraft 2 to supply fuel as a primary drive. Appropriate isolating valves are provided in the connections so that problem-free decoupling is possible.

Die Treibstofftanks haben ein großes Fassungsvermögen, damit die erreichbare Endgeschwindigkeit des abzu­ setzenden Fluggerätes 2 vergrößerbar ist.The fuel tanks have a large capacity so that the achievable top speed of the aircraft 2 to be set down can be increased.

Claims (2)

1. Wiederverwendbarer Tragkörper mit aerodynamischen Auftriebsmitteln, zur Starthilfe eines mit eigenem Triebwerk und Treibstofftanks ausgerüsteten Flug­ gerätes, z. B. Rakete, dadurch gekennzeichnet, daß der Tragkörper (1) ein Landefahrwerk (4) und Treib­ stofftanks zur Verbindung mit dem Triebwerk des Fluggerätes (2) aufweist, wobei dessen Triebwerk als Antrieb für die Gesamtanordnung vorgesehen ist und während der Transportphase ausschließlich aus den Treibstofftanks des Tragkörpers (1) versorgt wird.1. Reusable support body with aerodynamic buoyancy, to help launch a flight equipped with its own engine and fuel tanks, z. B. rocket, characterized in that the supporting body ( 1 ) has a landing gear ( 4 ) and propellant tanks for connection to the engine of the aircraft ( 2 ), the engine being provided as a drive for the overall arrangement and during the transport phase exclusively from the Fuel tanks of the support body ( 1 ) is supplied. 2. Vorrichtung nach Anspruch 1, dadurch gekennzeich­ net, daß das Fluggerät (2) unterhalb des Trag­ körpers (1) im Bereich des Landefahrwerks (4) ange­ ordnet ist.2. Apparatus according to claim 1, characterized in that the aircraft ( 2 ) below the supporting body ( 1 ) in the landing gear ( 4 ) is arranged.
DE19545711A 1995-12-07 1995-12-07 Reusable carrier body as starting aid for flight craft Expired - Fee Related DE19545711C1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE19545711A DE19545711C1 (en) 1995-12-07 1995-12-07 Reusable carrier body as starting aid for flight craft
EP96118411A EP0778200A3 (en) 1995-12-07 1996-11-16 Multi-stage space transport system and method for horizontal-takeoff
RU96122836A RU2120398C1 (en) 1995-12-07 1996-12-04 Multi-stage transport system at horizontal start for space flight and method of launching it
JP8326982A JPH09175499A (en) 1995-12-07 1996-12-06 Multi-stage type space flight and transporting device, and method for horizontal take-off employing the device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19545711A DE19545711C1 (en) 1995-12-07 1995-12-07 Reusable carrier body as starting aid for flight craft

Publications (1)

Publication Number Publication Date
DE19545711C1 true DE19545711C1 (en) 1997-06-05

Family

ID=7779482

Family Applications (1)

Application Number Title Priority Date Filing Date
DE19545711A Expired - Fee Related DE19545711C1 (en) 1995-12-07 1995-12-07 Reusable carrier body as starting aid for flight craft

Country Status (1)

Country Link
DE (1) DE19545711C1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3981691A1 (en) 2020-10-09 2022-04-13 ArianeGroup GmbH Carrier rocket system with carrier rocket and starting assistance unit

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3740645A1 (en) * 1987-12-01 1989-06-15 Dornier Gmbh Multistage space transportation system

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3740645A1 (en) * 1987-12-01 1989-06-15 Dornier Gmbh Multistage space transportation system

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3981691A1 (en) 2020-10-09 2022-04-13 ArianeGroup GmbH Carrier rocket system with carrier rocket and starting assistance unit
DE102020126575A1 (en) 2020-10-09 2022-04-14 Arianegroup Gmbh Launcher system with launcher and booster unit
DE102020126575B4 (en) 2020-10-09 2024-03-14 Arianegroup Gmbh Launch vehicle system with launcher and launch aid unit

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Legal Events

Date Code Title Description
8100 Publication of patent without earlier publication of application
D1 Grant (no unexamined application published) patent law 81
8364 No opposition during term of opposition
8327 Change in the person/name/address of the patent owner

Owner name: DAIMLERCHRYSLER AEROSPACE AKTIENGESELLSCHAFT, 8099

8327 Change in the person/name/address of the patent owner

Owner name: ASTRIUM GMBH, 85521 OTTOBRUNN, DE

8339 Ceased/non-payment of the annual fee