ISO 16694:2015
(Main)Space systems — The measured parameters at firing bench and flight tests of liquid rocket engines
Space systems — The measured parameters at firing bench and flight tests of liquid rocket engines
ISO 16694:2015 applies to all types of liquid rocket engines for expendable launch systems and satellites: a) Combustible fuel (including cryogenic); b) Large-thrust, multiple component engines, with and without afterburning; c) Low-thrust engines, one component (mono-propellant) and two-component (bi-propellant). This International Standard establishes a list of parameters to be measured and registered with the firing stand and flight tests of serial LRE. The order of preparation and carrying out of stand and flight tests, methods of processing, and analysis of tests results of liquid rocket engines, also measurement accuracy requirements are not regulated by this International Standard. Measurement accuracy requirements are established by engine designer. Parameters listed in this International Standard characterize performance attributes of liquid rocket engines and are used for evaluating of technical state of engines (operative, inoperative), if they correspond to the requirements specified and possibilities of putting them into operation. There are parameters specified in this International Standard, obligatory for registration and optional ones. The manufacturer of liquid rocket engines can determine additional list of parameters for specific items taking into account their design and diagrammatical features. The meaning "optional parameter" denotes (in cases when a proper unit or a component can be the part of an engine) that according to the manufacturer's decision, measurements are allowed not to be made. Measurement of parameters at firing stand and flight tests of liquid rocket engines is be made by means of the same sensors if possible.
Systèmes spatiaux — Paramètres mesurés au banc d'allumage et essais de vol des moteurs à propergol liquide
General Information
Relations
Standards Content (Sample)
INTERNATIONAL ISO
STANDARD 16694
First edition
2015-03-01
Space systems — The measured
parameters at firing bench and flight
tests of liquid rocket engines
Systèmes spatiaux — Paramètres mesurés au banc d’allumage et
essais de vol des moteurs à propergol liquide
Reference number
©
ISO 2015
© ISO 2015
All rights reserved. Unless otherwise specified, no part of this publication may be reproduced or utilized otherwise in any form
or by any means, electronic or mechanical, including photocopying, or posting on the internet or an intranet, without prior
written permission. Permission can be requested from either ISO at the address below or ISO’s member body in the country of
the requester.
ISO copyright office
Case postale 56 • CH-1211 Geneva 20
Tel. + 41 22 749 01 11
Fax + 41 22 749 09 47
E-mail copyright@iso.org
Web www.iso.org
Published in Switzerland
ii © ISO 2015 – All rights reserved
Contents Page
Foreword .iv
Introduction .v
1 Scope . 1
2 Normative references . 1
3 Symbols and abbreviations . 1
4 General . 2
4.1 Classification of measured parameters . 2
4.2 Firing stand and flight tests operation conditions . 3
5 The measured parameters at tests of LRE . 3
5.1 The measured parameters at firing stand test of LRE . 4
5.2 The measured parameters at flight tests of LRE . 4
Foreword
ISO (the International Organization for Standardization) is a worldwide federation of national standards
bodies (ISO member bodies). The work of preparing International Standards is normally carried out
through ISO technical committees. Each member body interested in a subject for which a technical
committee has been established has the right to be represented on that committee. International
organizations, governmental and non-governmental, in liaison with ISO, also take part in the work.
ISO collaborates closely with the International Electrotechnical Commission (IEC) on all matters of
electrotechnical standardization.
The procedures used to develop this document and those intended for its further maintenance are
described in the ISO/IEC Directives, Part 1. In particular the different approval criteria needed for the
different types of ISO documents should be noted. This document was drafted in accordance with the
editorial rules of the ISO/IEC Directives, Part 2 (see www.iso.org/directives).
Attention is drawn to the possibility that some of the elements of this document may be the subject of
patent rights. ISO shall not be held responsible for identifying any or all such patent rights. Details of any
patent rights identified during the development of the document will be in the Introduction and/or on
the ISO list of patent declarations received (see www.iso.org/patents).
Any trade name used in this document is information given for the convenience of users and does not
constitute an endorsement.
For an explanation on the meaning of ISO specific terms and expressions related to conformity
assessment, as well as information about ISO’s adherence to the WTO principles in the Technical Barriers
to Trade (TBT), see the following URL: Foreword — Supplementary information.
The committee responsible for this document is ISO/TC 20, Aircraft and space vehicles, Subcommittee
SC 14, Space systems and operations.
iv © ISO 2015 – All rights reserved
Introduction
This International Standard provides customers, designers, and manufacturers of liquid rocket engines
with general provisions to the parameters measured under firing stand tests, under break-in, and flight
tests. Parameters subjected to be measured are determined in the design documentation and are used
under the analysis of reliability and quality control of liquid rocket engines.
The determination of common requirements to the parameters of liquid rocket engines measured at
firing stand and flight tests on a global scale was developed:
— to provide the required quality and reliability of rocket engines being created and used;
— to compare tests results and engines impartially;
— to provide safety of final items and environmental protection.
This International Standard will allow the development of a common criteria of evaluating and comparing of
liquid rocket engines created by different countries according to the results of firing stand and flight tests.
INTERNATIONAL STANDARD ISO 16694:2015(E)
Space systems — The measured parameters at firing bench
and flight tests of liquid rocket engines
1 Scope
This International Standard applies to all types of liquid rocket engines for expendable launch systems
and satellites:
a) Combustible fuel (including cryogenic);
b) Large-thrust, multiple component engines, with and without afterburning;
c) Low-thrust engines, one component (mono-propellant) and two-component (bi-propellant).
This International Standard establishes a list of parameters to be measured and registered with the
firing stand and flight tests of serial LRE.
The order of preparation and carrying out of stand and flight tests, methods of processing, and analysis
of tests results of liquid rocket engines, also measurement accuracy requirements are not regulated by
this International Standard. Measurement accuracy requirements are established by engine designer.
Parameters listed in this International Standard characterize performance attributes of liquid rocket
engines and are used for evaluating of technical state of engines (operative, inoperative), if they
correspond to the requirements specified and possibilities of putting them into operation.
There are parameters specified in this International Standard, obligatory for registration and optional ones.
The manufacturer of liquid rocket engines can determine additional list of parameters for specific items
taking into account their design and diagrammatical features.
The meaning “optional parameter” denotes (in cases when a proper unit or a component can be the part
of an engine) that according to the manufacturer’s decision, measurements are allowed not to be made.
Measurement of parameters at firing stand and flight tests of liquid rocket engines is be made by means
of the same sensors if possible.
2 Normative references
The following documents, in whole or in part, are normatively referenced in this document and are
indispensable for its application. For dated references, only the edition cited applies. For undated
references, the latest edition of the referenced document (including any amendments) applies.
ISO 15864:2004, Space systems — General test methods for space craft, subsystems and units
ISO 15865:2005, Space systems — Qualification assessment
ISO 24917:2010, Space systems — General test requirements for launch vehicles
3 Symbols and abbreviations
AVR apparent velocity regulator
BTPU booster turbo pump
CFC components-flow controller
CST confirmatory sampling test
DD design documentation
EV electric valve
FCR regulator of fuel components ratio in combustion chamber
IDT interdepartmental tests
LV launch vehicle
LRE liquid rocket engine
LTE low thrust engine
PA pressure alarm
PS propulsion system
PST pressure stabilizer
SAT sampling acceptance test
SST special sampling test
SV space vehicle
TDS tank depletion system
TPU turbopump
TT technological test
4 General
4.1 Classification of measured parameters
4.1.1 The main purpose of measurement at proof tests of serial LRE (firing stand and flight tests) is to
provide information for reliability analysis and quality control of engines.
4.1.2 Parameters measured at firing stand and flight tests of LRE are subdivided into the following groups:
a) parameters characterizing test operation conditions;
b) main parameters;
c) parameters characterizing the engine ability to operate without any degradation.
4.1.3 Parameters that characterize the actual test operation conditions are compared to required test
operation conditions. These parameters include:
a) environmental parameters before and during the tests,
b) fuel components state before and during the tests, and
c) LRE characteristics (thrust and specific impulse).
2 © ISO 2015 – All rights reserved
4.1.4 The main parameters characterize the ability of an engine to fulfill requirements determined by
the technical documentation of the manufacturer.
4.1.5 Parameters characterizing the ability of an engine to operate without any degradation are used to
control the loads imposed over the engine elements.
This group consists of parameters whose values cannot be determined directly with measurements
made during the assembly production process. Among these parameters are ones characterizing
strength and heat-resistance of the combustion chamber and gas generator and the stability of working
process in these assemblies. In case of an emergency situation these parameters (together with the main
parameters and parameters characterizing the conditions of test operation) are used for the reasons of
emergency process analysis.
4.2 Firing stand and flight tests operation conditions
4.2.1 Qualification tests of LRE are carried out in order to verify a safety margin beyond the expected
life in accordance with the manufacturer of LV (SV) in consideration of the environmental factors and
engine operation modes.
4.2.2 Technological tests are carried out under values of the environmental factors and engine operation
mode with operating time necessary for measurement of parameters.
4.2.3 Sampling acceptance tests are performed for checking lifetime which is agreed upon with the
manufacturer of LV (SV) under values of the environmental factors and engine operation modes.
4.2.4 Confirmatory Sampling Test (CST) is carried out within the guarantee limits of the lifelength and
operation conditions of LRE. It is allowed to carry out CST above guarantee limits one at a time or under
any system of operation conditions of LRE.
4.2.5 Special tests of LRE are carried out in accordance with special programs defined by a designer or
a manufacturer of LRE and ratified by both enterprises.
4.2.6 Flight tests of LRE are carried out in a LV (SV) at the real conditions of operation with the purpose
of verifying conformance of LRE with specifications and determination of readiness of use.
4.2.7 Purposes and objectives of flight tests are presented in details in ISO 24917.
4.2.8 General methods of tests of spacecrafts, subsystems, and units are presented in ISO 15864.
4.2.9 Flight test analysis is performed according to the requirements of ISO 15865.
5 The measured parameters at tests of LRE
The measured parameters at firing stand and flight tests of LRE are presented in the respective tables.
LRE with afterburning (staged combustion cycle) and without afterburning (gas generator
cycle/expander cycle/pressure fed cycle) used in launch vehicles and space vehicles are represented.
Parameters measured under tests of LRE are subdivided into the following groups:
a) obligatory;
b) supplemental, depending on situation;
c) interchangeable, obligatory to be measured.
In the “Note” column in Tables 1 to 3, some necessary clarifications and additions to the specific
parameters are given.
5.1 The measured parameters at firing stand test of LRE
5.1.1 The measured parameters at commissioning and sampling tests (CTT, CST, and SST) of LRE are
presented in Table 1.
5.1.2 Table 2 is additional to Table 1 and contains parameters measured at qualification tests of LRE.
5.2 The measured parameters at flight tests of LRE
5.2.1 The measured parameters at flight tests of LRE are presented in Table 3.
The following symbols are used in the tables:
○ required parameter subjected to be obligatory measured;
• measuring of a parameter does not regulated by this International Standard;
Δ supplemental, depending on situation;
Х interchangeable parameter to be measured where m is a serial number of a parameter in the
m
respective table which can be used instead of the specified one in the clause.
Table 1 — The measured parameters at TT, SAT, CST, and SST
LRE type
without afterburn-
Description of a parameter with afterburning Note
ing
for LV for SV for LV for SV
1. Parameters characterizing test operation conditions
1.1 Ambient pressure ○ ○ ○ ○
1.2 Ambient temperature ○ ○ ○ ○
1.3 Ambient humidity Δ Δ Δ Δ
1.4 Direction and speed of air Δ Δ Δ Δ
1.5 Fuel components temperature in
the place of flow rate meters installa- ○ ○ ○ ○
tion and at the engine inlet
1.6 Chemical composition of the fuel
○ ○ ○ ○
co
...
Questions, Comments and Discussion
Ask us and Technical Secretary will try to provide an answer. You can facilitate discussion about the standard in here.